From 8cc53b33acfade687c84957073855d91f6ac1122 Mon Sep 17 00:00:00 2001 From: Alder Date: Sat, 11 Nov 2023 17:02:30 +0100 Subject: [PATCH] harmonize vehicle element base types --- examples/simpleAircraft.xml | 3502 +- examples/systemExample.xml | 1542 +- schema/cpacs_schema.xsd | 80431 +++++++++++++++++----------------- 3 files changed, 42715 insertions(+), 42760 deletions(-) diff --git a/examples/simpleAircraft.xml b/examples/simpleAircraft.xml index 96b4d7b..0a7724f 100644 --- a/examples/simpleAircraft.xml +++ b/examples/simpleAircraft.xml @@ -1,1751 +1,1751 @@ - -
- Simple aircraft template - 1.0.0 - - - DLR-SL - 2021-10-29T11:56:46.259694 - A simple, unrealistic, aircraft example - 3.4 - - -
- - - - Rotor models - - 1 - 1 - - 0.0 - 0.0 - 0.0 - - - - - Propeller - propeller - - - 1 - 1 - 1 - - - 0 - -90 - 0 - - - 2.5 - 1 - 0.5 - - - - PropellerHub - rigid - - - 5 - - - Propeller_pitchHinge - - - 0.10 - 0 - 0 - - - pitch - 10 - - - Propeller_blade - - - - 3300 - - - Propeller 2 - propeller - - - 0.5 - 0.5 - 0.5 - - - 0 - -90 - 0 - - - 2.9 - 3.5 - 0.5 - - - - PropellerHub - rigid - - - 5 - - - Propeller_pitchHinge - - - 0.10 - 0 - 0 - - - pitch - 10 - - - Propeller_blade - - - - 3300 - - - - - Propeller_blade - - - 1 - 1 - 1 - - - 0 - 0 - 0 - - - 0 - 0 - 0 - - - -
- Propeller_blade_section1 - - - 0.07 - 0.07 - 0.07 - - - 14.56 - 0 - 10 - - - 0 - 0 - 0 - - - - - Propeller_blade_section1_element_1 - NACA0010 - - - 1 - 1 - 1.75 - - - 0 - 0 - -90 - - - 0 - 0.5 - 0 - - - - -
-
- Propeller_blade_section5 - - - 0.1 - 0.1 - 0.1 - - - 5.97 - 0 - -11.42 - - - - - Propeller_blade_section5_element1 - NACA0010 - - - 1 - 1 - 0.39 - - - 0 - 0 - -90 - - - 0 - 0.5 - 0 - - - - -
-
- Propeller_blade_section10 - - - 0.03 - 0.03 - 0.03 - - - -9.18 - 0 - 0 - - - 0 - 0 - 0 - - - - - Propeller_blade_section10_element1 - NACA0010 - - - 1 - 1 - 0.18 - - - 0 - 0 - -90 - - - 0 - 0.5 - 0 - - - - -
- - - - Propeller_blade_positioning1 - 0.05 - 90 - 0 - Propeller_blade_section1 - - - Propeller_blade_positioning2 - 0.2 - 90 - 0 - Propeller_blade_section1 - Propeller_blade_section5 - - - Propeller_blade_positioning3 - 0.3 - 90 - 0 - Propeller_blade_section5 - Propeller_blade_section10 - - - - - Propeller_blade_segment1 - Propeller_blade_section1_element1 - Propeller_blade_section5_element1 - - - Propeller_blade_segment2 - Propeller_blade_section5_element1 - Propeller_blade_section10_element1 - - - - - - - - - Aircraft model - The "model" is the singular form of aircraft. - - 1 - 1 - - 0 - 0 - 0 - - - - - Seat - fuselage - - - 0.4 - 0.4 - 0.4 - - - 6 - 2.2 - - - 90 - -90 - - - seat.stp - - - - - Fuselage - In this example, the aircraft fuselage represents the hierarchically topmost element. This can be seen from the fact that the fuselage does not have an element called parentUID. - - - 1.0 - 1.0 - 1.0 - - - 0.0 - 0.0 - 0.0 - - - -
- Section1 - - - 1.0 - 1.0 - 1.0 - - - - - Section 1 - fuselageCircleProfile - - - 0.01 - 0.01 - 0.01 - - - -0.2 - - - - -
-
- Section2 - - - 1.0 - 1.0 - 1.0 - - - - - Section 2 - fuselageCircleProfile - - - 0.5 - 0.5 - 0.5 - - - - -
-
- Section3 - - - 1.0 - 1.0 - 1.0 - - - - - Section 3 - fuselageCircleProfile - - - 0.5 - 0.5 - 0.5 - - - - -
-
- Section 4 - - - 1.0 - 1.0 - 1.0 - - - - - Section4 - fuselageCircleProfile - - - 0.1 - 0.1 - 0.1 - - - 0.4 - - - - -
- - - - Positioning2 - 1 - 90 - 0 - Section2ID - - - Positioning3 - 3 - 90 - 0 - Section2ID - Section3ID - - - Positioning4 - 2.5 - 90 - 0 - Section3ID - Section4ID - - - - - Segment1 - Section1IDElement1 - Section2IDElement1 - - - Guide Curve 1 - guideCurveUpperSegment1_gcp - 0.0 - 0 - - - Guide Curve 1 - guideCurveBBSegment1_gcp - 0.25 - 0.25 - - - Guide Curve 1 - guideCurveLowerSegment1_gcp - 0.5 - 0.5 - - - Guide Curve 1 - guideCurveRBSegment1_gcp - 0.75 - 0.75 - - - - - Segment2 - Section2IDElement1 - Section3IDElement1 - - - Guide Curve 1 - guideCurveUpperSegment2_gcp - guideCurveSegment1_1 - 0 - - - Guide Curve 1 - guideCurveBBSegment2_gcp - guideCurveSegment1_2 - 0.25 - - - Guide Curve 1 - guideCurveLowerSegment2_gcp - guideCurveSegment1_3 - 0.5 - - - Guide Curve 1 - guideCurveRBSegment2_gcp - guideCurveSegment1_4 - 0.75 - - - - - Segment3 - Section3IDElement1 - Section4IDElement1 - - - Guide Curve 1 - guideCurveUpperSegment3_gcp - guideCurveSegment2_1 - 0.0 - - - Guide Curve 1 - guideCurveBBSegment3_gcp - guideCurveSegment2_2 - C1 from previous - 0.25 - - - Guide Curve 1 - guideCurveLowerSegment3_gcp - guideCurveSegment2_3 - C1 from previous - 0.5 - - - Guide Curve 1 - guideCurveRBSegment3_gcp - guideCurveSegment2_4 - C1 from previous - 0.75 - - - - - - - Fairing - Wing - - - 1 - 1 - 1 - - - -0.25 - -0.1 - - - -
- Fairing section 1 - - - 1 - 1 - 1 - - - - - Fairing section 1 element 1 - fairingProfile - - - 1 - 0.25 - 0.1 - - - - -
-
- Fairing section 2 - - - 1 - 1 - 1 - - - 1.5 - - - - - Fairing section 2 element 1 - fairingProfile - - - 1 - 0.25 - 0.1 - - - - -
- - - - Fairing segment - fairing_sec1_el1 - fairing_sec2_el1 - - - Fairing guide curve 1 - fairing_gc1_profile - 0 - 0 - - - Fairing guide curve 1 - fairing_gc2_profile - 0.15 - 0.15 - - - Fairing guide curve 1 - fairing_gc3_profile - 0.25 - 0.25 - - - Fairing guide curve 1 - fairing_gc4_profile - 0.5 - 0.5 - - - Fairing guide curve 1 - fairing_gc5_profile - 0.75 - 0.75 - - - Fairing guide curve 1 - fairing_gc6_profile - 0.85 - 0.85 - - - - - - - - - Wing - fuselage - - - 1 - 1 - 1 - - - 2.8 - 0 - 0.5 - - - -
- Wing Section 1 - - - 1 - 1 - 1 - - - - - Wing Section 1 Main Element - NACA0012 - - - 1 - 1 - 1 - - - - -
-
- Wing Section 2 - - - 1 - 1 - 1 - - - - - Wing Section 2 Main Element - NACA0012 - - - 1 - 1 - 1 - - - - -
-
- Wing Section 3 - - - 1 - 1 - 1 - - - - - Wing Section 3 Main Element - NACA0012 - - - 0.5 - 0.5 - 0.5 - - - - -
- - - - Wing Section 2 Positioning - 0.5 - 2 - 0 - Wing_Sec2 - - - Wing Section 3 Positioning - 3 - 5 - 0 - Wing_Sec2 - Wing_Sec3 - - - - - Wing segment 1 - Segment from Wing Section 1 Main Element to Wing Section 2 Main Element - Wing_Sec1_El1 - Wing_Sec2_El1 - - - Wing segment 2 - Segment from Wing Section 2 Main Element to Wing Section 3 Main Element - Wing_Sec2_El1 - Wing_Sec3_El1 - - - - - Wing segment - This is a segment within the wing to specify internal structures and control surfaces. It was introduced to allow a different view on the wing from an aerodynamics and structures perspective. - Wing_Sec1_El1 - Wing_Sec3_El1 - - - - - aluminium7150 - 0.003 - - - - - - - aluminium2024 - 0.003 - - - - - - - - 0.0 - 0.2 - Wing_CompSeg - - - - - 0.2 - 0.17 - Wing_CompSeg - - - - - 1.0 - 0.2 - Wing_CompSeg - - - - - 0.0 - 0.6 - Wing_CompSeg - - - - - 0.2 - 0.59 - Wing_CompSeg - - - - - 1.0 - 0.6 - Wing_CompSeg - - - - - - Front spar - - Wing_CS_spar1_Pos1 - Wing_CS_spar1_Pos2 - Wing_CS_spar1_Pos3 - - - - - aluminium2024 - - 0.0 - - 0.0 - - - - Rear spar - - Wing_CS_spar2_Pos1 - Wing_CS_spar2_Pos2 - Wing_CS_spar2_Pos3 - - - - - aluminium2024 - - 0.0 - - 0.0 - - - - - - - Wing_CS_RibDef1 - - - 0.05 - leadingEdge - - - 0.95 - leadingEdge - - Wing_CS_spar1 - Wing_CS_spar2 - 10 - leadingEdge - cross - - 90 - - - - - aluminium2024 - - - - - Wing_CS_RibDef2 - - - 0.5 - 0.0 - Wing_CompSeg - - - 0.5 - trailingEdge - - leadingEdge - trailingEdge - - - - aluminium2024 - - - - - - - - - Aileron - Wing_CompSeg - - - - 0.7 - Wing_CompSeg - - - 0.7 - Wing_CompSeg - - - 0.8 - Wing_CompSeg - - - - - 0.96 - Wing_CompSeg - - - 0.96 - Wing_CompSeg - - - 0.8 - Wing_CompSeg - - - - - - 0.8 - 0.5 - - - 0.8 - 0.5 - - - - -1 - -25 - - - 0 - 0 - - - 1 - 15 - - - - - - - - - - - Vertical tailplane - fuselage - - - 1 - 1 - 1 - - - 5.2 - 0.02 - 0.46 - - - 90 - - - -
- Vertical Tailplane Section 1 - - - 1 - 1 - 1 - - - - - Vertical Tailplane Section 1 Main Element - NACA0012 - - - 1 - 1 - 1 - - - - -
-
- Vertical Tailplane Section 2 - - - 1 - 1 - 1 - - - - - Vertical Tailplane Section 2 Main Element - NACA0012 - - - 0.5 - 0.5 - 0.5 - - - - -
- - - - Vertical Tailplane Section Positioning - 1.5 - 45 - 5 - vTP_Sec2 - - - - - Segment from TP Section 1 Main Element to TP Section 2 Main Element - vTP_Sec1_El1 - vTP_Sec2_El1 - - - TP leading edge guide curve 1 - TP_trailingEdge_gcp - -1.0 - -1.0 - - - TP leading edge guide curve 1 - TP_leadingEdge_gcp - 0.0 - 0 - - - TP trailing edge guide curve 1 - TP_trailingEdge_gcp - 1 - 1 - - - - - - - Tailplane - verticalTailplane - - - 1 - 1 - 1 - - - 0.7 - 0.4 - - - -
- TP Section 1 - - - 1 - 1 - 1 - - - - - TP Section 1 Main Element - NACA0012 - - - 0.5 - 0.5 - 0.5 - - - - -
-
- TP Section 2 - - - 1 - 1 - 1 - - - - - TP Section 2 Main Element - NACA0012 - - - 0.25 - 0.25 - 0.25 - - - - -
- - - - TP Section Positioning - 1 - 22 - 5 - hTP_Sec2 - - - - - Segment from TP Section 1 Main Element to TP Section 2 Main Element - hTP_Sec1_El1 - hTP_Sec2_El1 - - - - - - - Wing - - - 90 - 0 - -90 - - - -0.4 - 1.0 - 0 - - - -
- Pylon section 1 - - - 0.0 - 0.0 - 0.0 - - - - - Pylon section 1 element 1 - PylonProfile - - - -
-
- Pylon Section 2 - - - 0.15 - 0.15 - 0.15 - - - - - Pylon section 2 element 1 - PylonProfile - - - 1 - 1 - 1 - - - - -
-
- Pylon Section 3 - - - 0.02 - 0.02 - 0.02 - - - - - Pylon section 3 element 1 - PylonProfile - - - 1 - 1 - 1 - - - - -
- - - - Pylon Position 1 - 0 - 0 - 0 - Pylon_Sec1 - - - Pylon Position 2 - 0.2 - 0 - 0 - Pylon_Sec1 - Pylon_Sec2 - - - Pylon Position 3 - 1 - 0 - 0 - Pylon_Sec2 - Pylon_Sec3 - - - - - Pylon Segment 1 - Pylon_Sec1_El1 - Pylon_Sec2_El1 - - - Pylon Segment 2 - Pylon_Sec2_El1 - Pylon_Sec3_El1 - - - - - Wing - - - 90 - 0 - -90 - - - 0 - 3.5 - 0 - - - 0.5 - 0.5 - 0.5 - - - -
- Pylon 2 section 1 - - - 0.0 - 0.0 - 0.0 - - - - - Pylon 2 Section 1 Main Element - PylonProfile - - - -
-
- Pylon 2 Section 2 - - - 0.15 - 0.15 - 0.15 - - - - - Pylon 2 Section 2 Main Element - PylonProfile - - - 1 - 1 - 1 - - - - -
-
- Pylon 2 Section 3 - - - 0.02 - 0.02 - 0.02 - - - - - Pylon 2 Section 3 Main Element - PylonProfile - - - 1 - 1 - 1 - - - - -
- - - - Pylon 2 Position 1 - 0 - 0 - 0 - Pylon2_Sec1 - - - Pylon 2 Position 2 - 0.2 - 0 - 0 - Pylon2_Sec1 - Pylon2_Sec2 - - - Pylon 2 Position 3 - 1 - 0 - 0 - Pylon2_Sec2 - Pylon2_Sec3 - - - - - Pylon 2 Segment 1 - Pylon2_Sec1_El1 - Pylon2_Sec2_El1 - - - Pylon 2 Segment 2 - Pylon2_Sec2_El1 - Pylon2_Sec3_El1 - - - - - - - - Generic System - - - Cube - predefinedCube - - - 0.4 - 0.3 - 0.2 - - - 4.5 - 0.3 - - - - - - - - - - Pylon - engine - myInstalledEngine - - - 1 - 1 - 1 - - - - - - - - - myEngine - - - - - - NACA0.00.00.12 - NACA 4 Series Profile - - 1.0;0.9875;0.975;0.9625;0.95;0.9375;0.925;0.9125;0.9;0.8875;0.875;0.8625;0.85;0.8375;0.825;0.8125;0.8;0.7875;0.775;0.7625;0.75;0.7375;0.725;0.7125;0.7;0.6875;0.675;0.6625;0.65;0.6375;0.625;0.6125;0.6;0.5875;0.575;0.5625;0.55;0.5375;0.525;0.5125;0.5;0.4875;0.475;0.4625;0.45;0.4375;0.425;0.4125;0.4;0.3875;0.375;0.3625;0.35;0.3375;0.325;0.3125;0.3;0.2875;0.275;0.2625;0.25;0.2375;0.225;0.2125;0.2;0.1875;0.175;0.1625;0.15;0.1375;0.125;0.1125;0.1;0.0875;0.075;0.0625;0.05;0.0375;0.025;0.0125;0.0;0.0125;0.025;0.0375;0.05;0.0625;0.075;0.0875;0.1;0.1125;0.125;0.1375;0.15;0.1625;0.175;0.1875;0.2;0.2125;0.225;0.2375;0.25;0.2625;0.275;0.2875;0.3;0.3125;0.325;0.3375;0.35;0.3625;0.375;0.3875;0.4;0.4125;0.425;0.4375;0.45;0.4625;0.475;0.4875;0.5;0.5125;0.525;0.5375;0.55;0.5625;0.575;0.5875;0.6;0.6125;0.625;0.6375;0.65;0.6625;0.675;0.6875;0.7;0.7125;0.725;0.7375;0.75;0.7625;0.775;0.7875;0.8;0.8125;0.825;0.8375;0.85;0.8625;0.875;0.8875;0.9;0.9125;0.925;0.9375;0.95;0.9625;0.975;0.9875;1.0 - 0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0 - -0.00126;-0.0030004180415;-0.00471438572941;-0.00640256842113;-0.00806559133343;-0.00970403933653;-0.0113184567357;-0.0129093470398;-0.0144771727147;-0.0160223549226;-0.0175452732434;-0.0190462653789;-0.0205256268372;-0.0219836105968;-0.0234204267471;-0.024836242105;-0.0262311798047;-0.0276053188583;-0.0289586936852;-0.0302912936071;-0.0316030623052;-0.0328938972373;-0.0341636490097;-0.0354121207001;-0.0366390671268;-0.0378441940595;-0.0390271573644;-0.0401875620783;-0.0413249614032;-0.042438855614;-0.043528690869;-0.0445938579126;-0.0456336906587;-0.04664746464;-0.0476343953088;-0.0485936361694;-0.0495242767241;-0.0504253402064;-0.0512957810767;-0.0521344822472;-0.0529402520006;-0.0537118205596;-0.0544478362583;-0.0551468612564;-0.0558073667285;-0.0564277274483;-0.0570062156697;-0.0575409941929;-0.0580301084765;-0.0584714776309;-0.0588628840933;-0.059201961739;-0.0594861821311;-0.0597128385384;-0.059879027262;-0.0599816256958;-0.060017266394;-0.059982306219;-0.05987278938;-0.0596844028137;-0.059412421875;-0.059051643633;-0.0585963041308;-0.0580399746271;-0.0573754299024;-0.0565944788455;-0.0556877432118;-0.054644363746;-0.0534516022043;-0.0520942903127;-0.0505540468987;-0.0488081315259;-0.0468277042382;-0.0445750655553;-0.0419990347204;-0.0390266537476;-0.0355468568262;-0.0313738751622;-0.0261471986426;-0.0189390266528;0.0;0.0189390266528;0.0261471986426;0.0313738751622;0.0355468568262;0.0390266537476;0.0419990347204;0.0445750655553;0.0468277042382;0.0488081315259;0.0505540468987;0.0520942903127;0.0534516022043;0.054644363746;0.0556877432118;0.0565944788455;0.0573754299024;0.0580399746271;0.0585963041308;0.059051643633;0.059412421875;0.0596844028137;0.05987278938;0.059982306219;0.060017266394;0.0599816256958;0.059879027262;0.0597128385384;0.0594861821311;0.059201961739;0.0588628840933;0.0584714776309;0.0580301084765;0.0575409941929;0.0570062156697;0.0564277274483;0.0558073667285;0.0551468612564;0.0544478362583;0.0537118205596;0.0529402520006;0.0521344822472;0.0512957810767;0.0504253402064;0.0495242767241;0.0485936361694;0.0476343953088;0.04664746464;0.0456336906587;0.0445938579126;0.043528690869;0.042438855614;0.0413249614032;0.0401875620783;0.0390271573644;0.0378441940595;0.0366390671268;0.0354121207001;0.0341636490097;0.0328938972373;0.0316030623052;0.0302912936071;0.0289586936852;0.0276053188583;0.0262311798047;0.024836242105;0.0234204267471;0.0219836105968;0.0205256268372;0.0190462653789;0.0175452732434;0.0160223549226;0.0144771727147;0.0129093470398;0.0113184567357;0.00970403933653;0.00806559133343;0.00640256842113;0.00471438572941;0.0030004180415;0.00126 - - - - Engine pylon circle profile - - 0.5;0.4;0.3;0.2;0.1;0;-0.1;-0.2;-0.3;-0.4;-0.5;-0.4;-0.3;-0.2;-0.1;0;0.1;0.2;0.3;0.4;0.5 - 0;0;0;0;0;0;0;0;0;0;0;0;0;0;0;0;0;0;0;0;0 - 0;-0.3;-0.4;-0.458257569;-0.489897949;-0.5;-0.489897949;-0.458257569;-0.4;-0.3;0;0.3;0.4;0.458257569;0.489897949;0.5;0.489897949;0.458257569;0.4;0.3;0 - - - - - - Circle - Profile build up from set of Points on Circle where may Dimensions are 1..-1 - - 0.0;0.0;0.0;0.0;0.0 - 0.0;1.0;0.0;-1.0;0.0 - 1.0;0.0;-1.0;0.0;1.0 - - - - Fairing profile - Profile build up from set of Points on Circle where may Dimensions are 1..-1 - - 0.0;0.0;0.0;0.0;0.0 - 0.0;1.0;0.0;-1.0;0.0 - 0.1;-0.5;0.0;-0.5;0.1 - - - - - - Lower guide curve - - -0.8;-0.15 - 0.05;0.5 - 0.0;0.0 - - - - Lower guide curve - - 0.0 - 0.5 - 0.0 - - - - Lower guide curve - - -0.4;-0.1 - 0.5;0.9 - 0.0;0.0 - - - - Lower guide curve - - 0.0;0.0 - 0.1;0.5 - 0.9;0.3 - - - - Lower guide curve - - 0.0 - 0.5 - 0.0 - - - - Lower guide curve - - 0.0;0.0 - 0.5;0.75 - 0.1;0.1 - - - - Lower guide curve - - 0.0;0.0 - 0.1;0.5 - -0.9;-0.3 - - - - Lower guide curve - - 0.0 - 0.5 - 0.0 - - - - Lower guide curve - - 0.0;0.0 - 0.5;0.75 - -0.1;-0.1 - - - - Lower guide curve - - 0.5;0.1 - 0.2;0.75 - 0.0;0.0 - - - - Lower guide curve - - 0.0;0.0;0.0;0.0;0.0;0.0;0.0 - 0.05;0.1;0.2;0.5;0.8;0.9;0.95 - 0.0;0.0;0.0;0.0;0.0;0.0;0.0 - - - - Lower guide curve - - 0.0;0.0;0.0;0.0;0.0;0.0;0.0 - 0.05;0.1;0.2;0.5;0.8;0.9;0.95 - 0.0;0.0;0.0;0.0;0.0;0.0;0.0 - - - - Tailplane leading edge profile - - 0.15 - 0.2 - 0.0 - - - - Tailplane trailing edge profile - - 0.1;-0.05 - 0.2;0.8 - 0.0;0.0 - - - - Fairing guide curve 1 profile - - 0.5;0.65;0.4 - 0.05;0.5;0.9 - 0.0;0.0;0.0 - - - - Fairing guide curve 1 profile - - 0.55;0.65;0.4 - 0.1;0.5;0.9 - 0.1;0.1;0.1 - - - - Fairing guide curve 2 profile - - 0.0;0.0;0.0 - 0.1;0.5;0.9 - 0.0;0.0;0.0 - - - - Fairing guide curve 3 profile - - 0.0;0.0;0.0;0.0;0.0;0.0;0.0 - 0.05;0.1;0.2;0.5;0.8;0.9;0.95 - 0.0;0.0;0.0;0.0;0.0;0.0;0.0 - - - - Fairing guide curve 4 profile - - 0.0;0.0;0.0 - 0.05;0.5;0.95 - 0.0;0.0;0.0 - - - - Fairing guide curve 4 profile - - 0.55;0.65;0.4 - 0.1;0.5;0.9 - -0.1;-0.1;-0.1 - - - - - - NACA0.00.00.10 - NACA 4 Series Profile - - 1.0;0.9875;0.975;0.9625;0.95;0.9375;0.925;0.9125;0.9;0.8875;0.875;0.8625;0.85;0.8375;0.825;0.8125;0.8;0.7875;0.775;0.7625;0.75;0.7375;0.725;0.7125;0.7;0.6875;0.675;0.6625;0.65;0.6375;0.625;0.6125;0.6;0.5875;0.575;0.5625;0.55;0.5375;0.525;0.5125;0.5;0.4875;0.475;0.4625;0.45;0.4375;0.425;0.4125;0.4;0.3875;0.375;0.3625;0.35;0.3375;0.325;0.3125;0.3;0.2875;0.275;0.2625;0.25;0.2375;0.225;0.2125;0.2;0.1875;0.175;0.1625;0.15;0.1375;0.125;0.1125;0.1;0.0875;0.075;0.0625;0.05;0.0375;0.025;0.0125;0.0;0.0125;0.025;0.0375;0.05;0.0625;0.075;0.0875;0.1;0.1125;0.125;0.1375;0.15;0.1625;0.175;0.1875;0.2;0.2125;0.225;0.2375;0.25;0.2625;0.275;0.2875;0.3;0.3125;0.325;0.3375;0.35;0.3625;0.375;0.3875;0.4;0.4125;0.425;0.4375;0.45;0.4625;0.475;0.4875;0.5;0.5125;0.525;0.5375;0.55;0.5625;0.575;0.5875;0.6;0.6125;0.625;0.6375;0.65;0.6625;0.675;0.6875;0.7;0.7125;0.725;0.7375;0.75;0.7625;0.775;0.7875;0.8;0.8125;0.825;0.8375;0.85;0.8625;0.875;0.8875;0.9;0.9125;0.925;0.9375;0.95;0.9625;0.975;0.9875;1.0 - 0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0 - 0.00105;0.002500348;0.003928655;0.005335474;0.006721326;0.008086699;0.009432047;0.010757789;0.012064311;0.013351962;0.014621061;0.015871888;0.017104689;0.018319675;0.019517022;0.020696868;0.021859317;0.023004432;0.024132245;0.025242745;0.026335885;0.027411581;0.028469708;0.029510101;0.030532556;0.031536828;0.032522631;0.033489635;0.034437468;0.035365713;0.036273909;0.037161548;0.038028076;0.038872887;0.039695329;0.040494697;0.041270231;0.042021117;0.042746484;0.043445402;0.044116877;0.04475985;0.045373197;0.045955718;0.046506139;0.047023106;0.04750518;0.047950828;0.048358424;0.048726231;0.049052403;0.049334968;0.049571818;0.049760699;0.049899189;0.049984688;0.050014389;0.049985255;0.049893991;0.049737002;0.049510352;0.049209703;0.048830253;0.048366646;0.047812858;0.047162066;0.046406453;0.04553697;0.044543002;0.043411909;0.042128372;0.040673443;0.039023087;0.037145888;0.034999196;0.032522211;0.029622381;0.026144896;0.021789332;0.015782522;0;-0.015782522;-0.021789332;-0.026144896;-0.029622381;-0.032522211;-0.034999196;-0.037145888;-0.039023087;-0.040673443;-0.042128372;-0.043411909;-0.044543002;-0.04553697;-0.046406453;-0.047162066;-0.047812858;-0.048366646;-0.048830253;-0.049209703;-0.049510352;-0.049737002;-0.049893991;-0.049985255;-0.050014389;-0.049984688;-0.049899189;-0.049760699;-0.049571818;-0.049334968;-0.049052403;-0.048726231;-0.048358424;-0.047950828;-0.04750518;-0.047023106;-0.046506139;-0.045955718;-0.045373197;-0.04475985;-0.044116877;-0.043445402;-0.042746484;-0.042021117;-0.041270231;-0.040494697;-0.039695329;-0.038872887;-0.038028076;-0.037161548;-0.036273909;-0.035365713;-0.034437468;-0.033489635;-0.032522631;-0.031536828;-0.030532556;-0.029510101;-0.028469708;-0.027411581;-0.026335885;-0.025242745;-0.024132245;-0.023004432;-0.021859317;-0.020696868;-0.019517022;-0.018319675;-0.017104689;-0.015871888;-0.014621061;-0.013351962;-0.012064311;-0.010757789;-0.009432047;-0.008086699;-0.006721326;-0.005335474;-0.003928655;-0.002500348;-0.00105 - - - - - - - - Pre-defined cube - - - 1 - 1 - 1 - - - - - - - - Aluminium 2024 - 2.8e3 - - 73.1e9 - 0.25574 - - - - Aluminium 7150 - 2.8e3 - - 1.0520897e11 - 0.3435 - 1.0520897e11 - 303336000 - - - - - + +
+ Simple aircraft template + 1.0.0 + + + DLR-SL + 2021-10-29T11:56:46.259694 + A simple, unrealistic, aircraft example + 3.4 + + +
+ + + + Rotor models + + 1 + 1 + + 0.0 + 0.0 + 0.0 + + + + + Propeller + propeller + + + 1 + 1 + 1 + + + 0 + -90 + 0 + + + 2.5 + 1 + 0.5 + + + + PropellerHub + rigid + + + 5 + + + Propeller_pitchHinge + + + 0.10 + 0 + 0 + + + pitch + 10 + + + Propeller_blade + + + + 3300 + + + Propeller 2 + propeller + + + 0.5 + 0.5 + 0.5 + + + 0 + -90 + 0 + + + 2.9 + 3.5 + 0.5 + + + + PropellerHub + rigid + + + 5 + + + Propeller_pitchHinge + + + 0.10 + 0 + 0 + + + pitch + 10 + + + Propeller_blade + + + + 3300 + + + + + Propeller_blade + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + +
+ Propeller_blade_section1 + + + 0.07 + 0.07 + 0.07 + + + 14.56 + 0 + 10 + + + 0 + 0 + 0 + + + + + Propeller_blade_section1_element_1 + NACA0010 + + + 1 + 1 + 1.75 + + + 0 + 0 + -90 + + + 0 + 0.5 + 0 + + + + +
+
+ Propeller_blade_section5 + + + 0.1 + 0.1 + 0.1 + + + 5.97 + 0 + -11.42 + + + + + Propeller_blade_section5_element1 + NACA0010 + + + 1 + 1 + 0.39 + + + 0 + 0 + -90 + + + 0 + 0.5 + 0 + + + + +
+
+ Propeller_blade_section10 + + + 0.03 + 0.03 + 0.03 + + + -9.18 + 0 + 0 + + + 0 + 0 + 0 + + + + + Propeller_blade_section10_element1 + NACA0010 + + + 1 + 1 + 0.18 + + + 0 + 0 + -90 + + + 0 + 0.5 + 0 + + + + +
+ + + + Propeller_blade_positioning1 + 0.05 + 90 + 0 + Propeller_blade_section1 + + + Propeller_blade_positioning2 + 0.2 + 90 + 0 + Propeller_blade_section1 + Propeller_blade_section5 + + + Propeller_blade_positioning3 + 0.3 + 90 + 0 + Propeller_blade_section5 + Propeller_blade_section10 + + + + + Propeller_blade_segment1 + Propeller_blade_section1_element1 + Propeller_blade_section5_element1 + + + Propeller_blade_segment2 + Propeller_blade_section5_element1 + Propeller_blade_section10_element1 + + + + + + + + + Aircraft model + The "model" is the singular form of aircraft. + + 1 + 1 + + 0 + 0 + 0 + + + + + Seat + fuselage + + + 0.4 + 0.4 + 0.4 + + + 6 + 2.2 + + + 90 + -90 + + + seat.stp + + + + + Fuselage + In this example, the aircraft fuselage represents the hierarchically topmost element. This can be seen from the fact that the fuselage does not have an element called parentUID. + + + 1.0 + 1.0 + 1.0 + + + 0.0 + 0.0 + 0.0 + + + +
+ Section1 + + + 1.0 + 1.0 + 1.0 + + + + + Section 1 + fuselageCircleProfile + + + 0.01 + 0.01 + 0.01 + + + -0.2 + + + + +
+
+ Section2 + + + 1.0 + 1.0 + 1.0 + + + + + Section 2 + fuselageCircleProfile + + + 0.5 + 0.5 + 0.5 + + + + +
+
+ Section3 + + + 1.0 + 1.0 + 1.0 + + + + + Section 3 + fuselageCircleProfile + + + 0.5 + 0.5 + 0.5 + + + + +
+
+ Section 4 + + + 1.0 + 1.0 + 1.0 + + + + + Section4 + fuselageCircleProfile + + + 0.1 + 0.1 + 0.1 + + + 0.4 + + + + +
+ + + + Positioning2 + 1 + 90 + 0 + Section2ID + + + Positioning3 + 3 + 90 + 0 + Section2ID + Section3ID + + + Positioning4 + 2.5 + 90 + 0 + Section3ID + Section4ID + + + + + Segment1 + Section1IDElement1 + Section2IDElement1 + + + Guide Curve 1 + guideCurveUpperSegment1_gcp + 0.0 + 0 + + + Guide Curve 1 + guideCurveBBSegment1_gcp + 0.25 + 0.25 + + + Guide Curve 1 + guideCurveLowerSegment1_gcp + 0.5 + 0.5 + + + Guide Curve 1 + guideCurveRBSegment1_gcp + 0.75 + 0.75 + + + + + Segment2 + Section2IDElement1 + Section3IDElement1 + + + Guide Curve 1 + guideCurveUpperSegment2_gcp + guideCurveSegment1_1 + 0 + + + Guide Curve 1 + guideCurveBBSegment2_gcp + guideCurveSegment1_2 + 0.25 + + + Guide Curve 1 + guideCurveLowerSegment2_gcp + guideCurveSegment1_3 + 0.5 + + + Guide Curve 1 + guideCurveRBSegment2_gcp + guideCurveSegment1_4 + 0.75 + + + + + Segment3 + Section3IDElement1 + Section4IDElement1 + + + Guide Curve 1 + guideCurveUpperSegment3_gcp + guideCurveSegment2_1 + 0.0 + + + Guide Curve 1 + guideCurveBBSegment3_gcp + guideCurveSegment2_2 + C1 from previous + 0.25 + + + Guide Curve 1 + guideCurveLowerSegment3_gcp + guideCurveSegment2_3 + C1 from previous + 0.5 + + + Guide Curve 1 + guideCurveRBSegment3_gcp + guideCurveSegment2_4 + C1 from previous + 0.75 + + + + + + + Fairing + Wing + + + 1 + 1 + 1 + + + -0.25 + -0.1 + + + +
+ Fairing section 1 + + + 1 + 1 + 1 + + + + + Fairing section 1 element 1 + fairingProfile + + + 1 + 0.25 + 0.1 + + + + +
+
+ Fairing section 2 + + + 1 + 1 + 1 + + + 1.5 + + + + + Fairing section 2 element 1 + fairingProfile + + + 1 + 0.25 + 0.1 + + + + +
+ + + + Fairing segment + fairing_sec1_el1 + fairing_sec2_el1 + + + Fairing guide curve 1 + fairing_gc1_profile + 0 + 0 + + + Fairing guide curve 1 + fairing_gc2_profile + 0.15 + 0.15 + + + Fairing guide curve 1 + fairing_gc3_profile + 0.25 + 0.25 + + + Fairing guide curve 1 + fairing_gc4_profile + 0.5 + 0.5 + + + Fairing guide curve 1 + fairing_gc5_profile + 0.75 + 0.75 + + + Fairing guide curve 1 + fairing_gc6_profile + 0.85 + 0.85 + + + + + + + + + Wing + fuselage + + + 1 + 1 + 1 + + + 2.8 + 0 + 0.5 + + + +
+ Wing Section 1 + + + 1 + 1 + 1 + + + + + Wing Section 1 Main Element + NACA0012 + + + 1 + 1 + 1 + + + + +
+
+ Wing Section 2 + + + 1 + 1 + 1 + + + + + Wing Section 2 Main Element + NACA0012 + + + 1 + 1 + 1 + + + + +
+
+ Wing Section 3 + + + 1 + 1 + 1 + + + + + Wing Section 3 Main Element + NACA0012 + + + 0.5 + 0.5 + 0.5 + + + + +
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+ + + + + + + + Pre-defined cube + + + 1 + 1 + 1 + + + + + + + + Aluminium 2024 + 2.8e3 + + 73.1e9 + 0.25574 + + + + Aluminium 7150 + 2.8e3 + + 1.0520897e11 + 0.3435 + 1.0520897e11 + 303336000 + + + + + diff --git a/examples/systemExample.xml b/examples/systemExample.xml index 6536c38..336e19d 100644 --- a/examples/systemExample.xml +++ b/examples/systemExample.xml @@ -1,772 +1,772 @@ - - -
- Example system architecture - 1.0.0 - - - DLR-SL - 2022-12-02T10:30:00 - Create initial data set - 3.5 - - -
- - - - Example aircraft - - - Engine left - engine - exampleAircraft - - - -5 - - - - - Engine right - engine - exampleAircraft - - - 5 - - - - - - - - Example system - - - heatExchanger1 - heatExchangerSystem1 - hx - - - heatExchanger2 - heatExchangerSystem2 - hx - - - heatExchangerGS - heatExchangerSystemGS - hx - - - gearbox1_inst - gearboxSystem1 - gearbox - - - motor1a_inst - motorSystem1a - eMotor - - - motor1b_inst - motorSystem1b - eMotor - - - gearbox2_inst - gearboxSystem2 - gearbox - - - motor2a_inst - motorSystem2a - eMotor - - - motor2b_inst - motorSystem2b - eMotor - - - generator_inst - generator - generator - - - gasturbine_inst - gasturbine - gasTurbine - - - - - - - - Example system - Example system with five components: propeller, gearbox, motor, generator and gas turbine - generic - - - motor1a_to_gb1 - - motor1a_inst - - - gb1_inst - - - - motor1b_to_gb1 - - motor1b_inst - - - gb1_inst - - - - motor1a_to_hx1 - - motor1a_inst - - - hx1_inst - - - - motor1b_to_hx1 - - motor1b_inst - - - hx1_inst - - - - gb1_to_hx1 - - gb1_inst - - - hx1_inst - - - - generator_to_motor1a - - generator_inst - - - motor1a_inst - - - - generator_to_motor1b - - generator_inst - - - motor1b_inst - - - - gasturbine_to_generator - - gasturbine_inst - - - generator_inst - - - - gasturbine_to_hxGS - - gasturbine_inst - - - hxGS_inst - - - - gb2_to_prop2 - - gb2_inst - - - eng2_inst - prop_inst - - - - gb1_to_prop1 - - gb1_inst - - - eng1_inst - prop_inst - - - - motor2a_to_gb2 - - motor2a_inst - - - gb2_inst - - - - motor2b_to_gb2 - - motor2b_inst - - - gb2_inst - - - - motor2a_to_hx2 - - motor2a_inst - - - hx2_inst - - - - motor2b_to_hx2 - - motor2b_inst - - - hx2_inst - - - - gb2_to_hx2 - - gb2_inst - - - hx2_inst - - - - generator_to_motor2a - - generator_inst - - - motor2a_inst - - - - generator_to_motor2b - - generator_inst - - - motor2b_inst - - - - generator_to_hxGS - - generator_inst - - - hxGS_inst - - - - fuelSystem_to_gasturbine - - ata28 - - - gasturbine_inst - - - - hxGS_to_ambient - - hxGS_inst - - - ambient - - - - hxGS_to_ambient - - hx1_inst - - - ambient - - - - hx2_to_ambient - - hx2_inst - - - ambient - - - - - - - - - - example - example power breakdown with 5 systems: propeller, gearbox, motor, generator and gas turbine - - 0. - 0. - - ISA - - - - - gb1_to_prop1 - gb1_to_prop1 - - - 6517047.11 - 73907.3 - - - - motor1a_to_gb1 - motor1a_to_gb1 - - 3392881.67 - 3847.7 - - - - motor1b_to_gb1 - motor1b_to_gb1 - - 3392881.67 - 3847.7 - - - - motor1a_to_hx1 - motor1a_to_hx1 - - 67857.6 - - - - motor1b_to_hx1 - motor1b_to_hx1 - - 67857.6 - - - - gb1_to_hx1 - gb1_to_hx1 - - 133000.9 - - - - generator_to_motor1a - generator_to_motor1a - - 3462124.15 - - - - generator_to_motor1b - generator_to_motor1b - - 3462124.15 - - - - gasturbine_to_generator - gasturbine_to_generator - - 13848496.61 - 13223.65 - - - - gasturbine_to_hxGS - gasturbine_to_hxGS - - 307744.36 - - - - generator_to_hxGS - generator_to_hxGS - - 276969.932 - - - - - - hxGS_to_ambient - hxGS_to_ambient - - 584714.301 - - - - hx1_to_ambient - hx1_to_ambient - - 268716.22 - - - - - - - - - - - - Engine - - - Propeller - - - 1 - 1 - 1 - - - 0 - -90 - 0 - - - 2.5 - 1 - 0.5 - - - - - - - - - - E-Motor - - - 1 - 2 - - - - - - - - Heat exchanger - - - 1 - 1 - 1 - - - - - - - Gear box - - - 0.56419 - 1 - 0.56419 - - - - - - - GasTurbine - - - 1 - 3 - 1 - - - - - - - Generator - - - 0.56419 - 1 - 0.56419 - - - - - - - - - Propeller_blade - - - 1 - 1 - 1 - - - 0 - 0 - 0 - - - 0 - 0 - 0 - - - -
- Propeller_blade_section1 - - - 0.07 - 0.07 - 0.07 - - - 14.56 - 0 - 10 - - - 0 - 0 - 0 - - - - - Propeller_blade_section1_element_1 - NACA0010 - - - 1 - 1 - 1.75 - - - 0 - 0 - -90 - - - 0 - 0.5 - 0 - - - - -
-
- Propeller_blade_section5 - - - 0.1 - 0.1 - 0.1 - - - 5.97 - 0 - -11.42 - - - - - Propeller_blade_section5_element1 - NACA0010 - - - 1 - 1 - 0.39 - - - 0 - 0 - -90 - - - 0 - 0.5 - 0 - - - - -
-
- Propeller_blade_section10 - - - 0.03 - 0.03 - 0.03 - - - -9.18 - 0 - 0 - - - 0 - 0 - 0 - - - - - Propeller_blade_section10_element1 - NACA0010 - - - 1 - 1 - 0.18 - - - 0 - 0 - -90 - - - 0 - 0.5 - 0 - - - - -
- - - - Propeller_blade_positioning1 - 0.05 - 90 - 0 - Propeller_blade_section1 - - - Propeller_blade_positioning2 - 0.2 - 90 - 0 - Propeller_blade_section1 - Propeller_blade_section5 - - - Propeller_blade_positioning3 - 0.3 - 90 - 0 - Propeller_blade_section5 - Propeller_blade_section10 - - - - - Propeller_blade_segment1 - Propeller_blade_section1_element1 - Propeller_blade_section5_element1 - - - Propeller_blade_segment2 - Propeller_blade_section5_element1 - Propeller_blade_section10_element1 - - - - - - - Propeller - - PropellerHub - rigid - - - 5 - - - Propeller_pitchHinge - - - 0.10 - 0 - 0 - - - pitch - 10 - - - Propeller_blade - - - - - - - - - - NACA0.00.00.10 - NACA 4 Series Profile - - 1.0;0.9875;0.975;0.9625;0.95;0.9375;0.925;0.9125;0.9;0.8875;0.875;0.8625;0.85;0.8375;0.825;0.8125;0.8;0.7875;0.775;0.7625;0.75;0.7375;0.725;0.7125;0.7;0.6875;0.675;0.6625;0.65;0.6375;0.625;0.6125;0.6;0.5875;0.575;0.5625;0.55;0.5375;0.525;0.5125;0.5;0.4875;0.475;0.4625;0.45;0.4375;0.425;0.4125;0.4;0.3875;0.375;0.3625;0.35;0.3375;0.325;0.3125;0.3;0.2875;0.275;0.2625;0.25;0.2375;0.225;0.2125;0.2;0.1875;0.175;0.1625;0.15;0.1375;0.125;0.1125;0.1;0.0875;0.075;0.0625;0.05;0.0375;0.025;0.0125;0.0;0.0125;0.025;0.0375;0.05;0.0625;0.075;0.0875;0.1;0.1125;0.125;0.1375;0.15;0.1625;0.175;0.1875;0.2;0.2125;0.225;0.2375;0.25;0.2625;0.275;0.2875;0.3;0.3125;0.325;0.3375;0.35;0.3625;0.375;0.3875;0.4;0.4125;0.425;0.4375;0.45;0.4625;0.475;0.4875;0.5;0.5125;0.525;0.5375;0.55;0.5625;0.575;0.5875;0.6;0.6125;0.625;0.6375;0.65;0.6625;0.675;0.6875;0.7;0.7125;0.725;0.7375;0.75;0.7625;0.775;0.7875;0.8;0.8125;0.825;0.8375;0.85;0.8625;0.875;0.8875;0.9;0.9125;0.925;0.9375;0.95;0.9625;0.975;0.9875;1.0 - 0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0 - 0.00105;0.002500348;0.003928655;0.005335474;0.006721326;0.008086699;0.009432047;0.010757789;0.012064311;0.013351962;0.014621061;0.015871888;0.017104689;0.018319675;0.019517022;0.020696868;0.021859317;0.023004432;0.024132245;0.025242745;0.026335885;0.027411581;0.028469708;0.029510101;0.030532556;0.031536828;0.032522631;0.033489635;0.034437468;0.035365713;0.036273909;0.037161548;0.038028076;0.038872887;0.039695329;0.040494697;0.041270231;0.042021117;0.042746484;0.043445402;0.044116877;0.04475985;0.045373197;0.045955718;0.046506139;0.047023106;0.04750518;0.047950828;0.048358424;0.048726231;0.049052403;0.049334968;0.049571818;0.049760699;0.049899189;0.049984688;0.050014389;0.049985255;0.049893991;0.049737002;0.049510352;0.049209703;0.048830253;0.048366646;0.047812858;0.047162066;0.046406453;0.04553697;0.044543002;0.043411909;0.042128372;0.040673443;0.039023087;0.037145888;0.034999196;0.032522211;0.029622381;0.026144896;0.021789332;0.015782522;0;-0.015782522;-0.021789332;-0.026144896;-0.029622381;-0.032522211;-0.034999196;-0.037145888;-0.039023087;-0.040673443;-0.042128372;-0.043411909;-0.044543002;-0.04553697;-0.046406453;-0.047162066;-0.047812858;-0.048366646;-0.048830253;-0.049209703;-0.049510352;-0.049737002;-0.049893991;-0.049985255;-0.050014389;-0.049984688;-0.049899189;-0.049760699;-0.049571818;-0.049334968;-0.049052403;-0.048726231;-0.048358424;-0.047950828;-0.04750518;-0.047023106;-0.046506139;-0.045955718;-0.045373197;-0.04475985;-0.044116877;-0.043445402;-0.042746484;-0.042021117;-0.041270231;-0.040494697;-0.039695329;-0.038872887;-0.038028076;-0.037161548;-0.036273909;-0.035365713;-0.034437468;-0.033489635;-0.032522631;-0.031536828;-0.030532556;-0.029510101;-0.028469708;-0.027411581;-0.026335885;-0.025242745;-0.024132245;-0.023004432;-0.021859317;-0.020696868;-0.019517022;-0.018319675;-0.017104689;-0.015871888;-0.014621061;-0.013351962;-0.012064311;-0.010757789;-0.009432047;-0.008086699;-0.006721326;-0.005335474;-0.003928655;-0.002500348;-0.00105 - - - - - + + +
+ Example system architecture + 1.0.0 + + + DLR-SL + 2022-12-02T10:30:00 + Create initial data set + 3.5 + + +
+ + + + Example aircraft + + + Engine left + engine + exampleAircraft + + + -5 + + + + + Engine right + engine + exampleAircraft + + + 5 + + + + + + + + Example system + + + heatExchanger1 + heatExchangerSystem1 + hx + + + heatExchanger2 + heatExchangerSystem2 + hx + + + heatExchangerGS + heatExchangerSystemGS + hx + + + gearbox1_inst + gearboxSystem1 + gearbox + + + motor1a_inst + motorSystem1a + eMotor + + + motor1b_inst + motorSystem1b + eMotor + + + gearbox2_inst + gearboxSystem2 + gearbox + + + motor2a_inst + motorSystem2a + eMotor + + + motor2b_inst + motorSystem2b + eMotor + + + generator_inst + generator + generator + + + gasturbine_inst + gasturbine + gasTurbine + + + + + + + + Example system + Example system with five components: propeller, gearbox, motor, generator and gas turbine + generic + + + motor1a_to_gb1 + + motor1a_inst + + + gb1_inst + + + + motor1b_to_gb1 + + motor1b_inst + + + gb1_inst + + + + motor1a_to_hx1 + + motor1a_inst + + + hx1_inst + + + + motor1b_to_hx1 + + motor1b_inst + + + hx1_inst + + + + gb1_to_hx1 + + gb1_inst + + + hx1_inst + + + + generator_to_motor1a + + generator_inst + + + motor1a_inst + + + + generator_to_motor1b + + generator_inst + + + motor1b_inst + + + + gasturbine_to_generator + + gasturbine_inst + + + generator_inst + + + + gasturbine_to_hxGS + + gasturbine_inst + + + hxGS_inst + + + + gb2_to_prop2 + + gb2_inst + + + eng2_inst + prop_inst + + + + gb1_to_prop1 + + gb1_inst + + + eng1_inst + prop_inst + + + + motor2a_to_gb2 + + motor2a_inst + + + gb2_inst + + + + motor2b_to_gb2 + + motor2b_inst + + + gb2_inst + + + + motor2a_to_hx2 + + motor2a_inst + + + hx2_inst + + + + motor2b_to_hx2 + + motor2b_inst + + + hx2_inst + + + + gb2_to_hx2 + + gb2_inst + + + hx2_inst + + + + generator_to_motor2a + + generator_inst + + + motor2a_inst + + + + generator_to_motor2b + + generator_inst + + + motor2b_inst + + + + generator_to_hxGS + + generator_inst + + + hxGS_inst + + + + fuelSystem_to_gasturbine + + ata28 + + + gasturbine_inst + + + + hxGS_to_ambient + + hxGS_inst + + + ambient + + + + hxGS_to_ambient + + hx1_inst + + + ambient + + + + hx2_to_ambient + + hx2_inst + + + ambient + + + + + + + + + + example + example power breakdown with 5 systems: propeller, gearbox, motor, generator and gas turbine + + 0. + 0. + + ISA + + + + + gb1_to_prop1 + gb1_to_prop1 + + + 6517047.11 + 73907.3 + + + + motor1a_to_gb1 + motor1a_to_gb1 + + 3392881.67 + 3847.7 + + + + motor1b_to_gb1 + motor1b_to_gb1 + + 3392881.67 + 3847.7 + + + + motor1a_to_hx1 + motor1a_to_hx1 + + 67857.6 + + + + motor1b_to_hx1 + motor1b_to_hx1 + + 67857.6 + + + + gb1_to_hx1 + gb1_to_hx1 + + 133000.9 + + + + generator_to_motor1a + generator_to_motor1a + + 3462124.15 + + + + generator_to_motor1b + generator_to_motor1b + + 3462124.15 + + + + gasturbine_to_generator + gasturbine_to_generator + + 13848496.61 + 13223.65 + + + + gasturbine_to_hxGS + gasturbine_to_hxGS + + 307744.36 + + + + generator_to_hxGS + generator_to_hxGS + + 276969.932 + + + + + + hxGS_to_ambient + hxGS_to_ambient + + 584714.301 + + + + hx1_to_ambient + hx1_to_ambient + + 268716.22 + + + + + + + + + + + + Engine + + + Propeller + + + 1 + 1 + 1 + + + 0 + -90 + 0 + + + 2.5 + 1 + 0.5 + + + + + + + + + + E-Motor + + + 1 + 2 + 1 + + + + + + + Heat exchanger + + + 1 + 1 + 1 + + + + + + + Gear box + + + 0.56419 + 1 + 0.56419 + + + + + + + GasTurbine + + + 1 + 3 + 1 + + + + + + + Generator + + + 0.56419 + 1 + 0.56419 + + + + + + + + + Propeller_blade + + + 1 + 1 + 1 + + + 0 + 0 + 0 + + + 0 + 0 + 0 + + + +
+ Propeller_blade_section1 + + + 0.07 + 0.07 + 0.07 + + + 14.56 + 0 + 10 + + + 0 + 0 + 0 + + + + + Propeller_blade_section1_element_1 + NACA0010 + + + 1 + 1 + 1.75 + + + 0 + 0 + -90 + + + 0 + 0.5 + 0 + + + + +
+
+ Propeller_blade_section5 + + + 0.1 + 0.1 + 0.1 + + + 5.97 + 0 + -11.42 + + + + + Propeller_blade_section5_element1 + NACA0010 + + + 1 + 1 + 0.39 + + + 0 + 0 + -90 + + + 0 + 0.5 + 0 + + + + +
+
+ Propeller_blade_section10 + + + 0.03 + 0.03 + 0.03 + + + -9.18 + 0 + 0 + + + 0 + 0 + 0 + + + + + Propeller_blade_section10_element1 + NACA0010 + + + 1 + 1 + 0.18 + + + 0 + 0 + -90 + + + 0 + 0.5 + 0 + + + + +
+ + + + Propeller_blade_positioning1 + 0.05 + 90 + 0 + Propeller_blade_section1 + + + Propeller_blade_positioning2 + 0.2 + 90 + 0 + Propeller_blade_section1 + Propeller_blade_section5 + + + Propeller_blade_positioning3 + 0.3 + 90 + 0 + Propeller_blade_section5 + Propeller_blade_section10 + + + + + Propeller_blade_segment1 + Propeller_blade_section1_element1 + Propeller_blade_section5_element1 + + + Propeller_blade_segment2 + Propeller_blade_section5_element1 + Propeller_blade_section10_element1 + + + + + + + Propeller + + PropellerHub + rigid + + + 5 + + + Propeller_pitchHinge + + + 0.10 + 0 + 0 + + + pitch + 10 + + + Propeller_blade + + + + + + + + + + NACA0.00.00.10 + NACA 4 Series Profile + + 1.0;0.9875;0.975;0.9625;0.95;0.9375;0.925;0.9125;0.9;0.8875;0.875;0.8625;0.85;0.8375;0.825;0.8125;0.8;0.7875;0.775;0.7625;0.75;0.7375;0.725;0.7125;0.7;0.6875;0.675;0.6625;0.65;0.6375;0.625;0.6125;0.6;0.5875;0.575;0.5625;0.55;0.5375;0.525;0.5125;0.5;0.4875;0.475;0.4625;0.45;0.4375;0.425;0.4125;0.4;0.3875;0.375;0.3625;0.35;0.3375;0.325;0.3125;0.3;0.2875;0.275;0.2625;0.25;0.2375;0.225;0.2125;0.2;0.1875;0.175;0.1625;0.15;0.1375;0.125;0.1125;0.1;0.0875;0.075;0.0625;0.05;0.0375;0.025;0.0125;0.0;0.0125;0.025;0.0375;0.05;0.0625;0.075;0.0875;0.1;0.1125;0.125;0.1375;0.15;0.1625;0.175;0.1875;0.2;0.2125;0.225;0.2375;0.25;0.2625;0.275;0.2875;0.3;0.3125;0.325;0.3375;0.35;0.3625;0.375;0.3875;0.4;0.4125;0.425;0.4375;0.45;0.4625;0.475;0.4875;0.5;0.5125;0.525;0.5375;0.55;0.5625;0.575;0.5875;0.6;0.6125;0.625;0.6375;0.65;0.6625;0.675;0.6875;0.7;0.7125;0.725;0.7375;0.75;0.7625;0.775;0.7875;0.8;0.8125;0.825;0.8375;0.85;0.8625;0.875;0.8875;0.9;0.9125;0.925;0.9375;0.95;0.9625;0.975;0.9875;1.0 + 0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0;0.0 + 0.00105;0.002500348;0.003928655;0.005335474;0.006721326;0.008086699;0.009432047;0.010757789;0.012064311;0.013351962;0.014621061;0.015871888;0.017104689;0.018319675;0.019517022;0.020696868;0.021859317;0.023004432;0.024132245;0.025242745;0.026335885;0.027411581;0.028469708;0.029510101;0.030532556;0.031536828;0.032522631;0.033489635;0.034437468;0.035365713;0.036273909;0.037161548;0.038028076;0.038872887;0.039695329;0.040494697;0.041270231;0.042021117;0.042746484;0.043445402;0.044116877;0.04475985;0.045373197;0.045955718;0.046506139;0.047023106;0.04750518;0.047950828;0.048358424;0.048726231;0.049052403;0.049334968;0.049571818;0.049760699;0.049899189;0.049984688;0.050014389;0.049985255;0.049893991;0.049737002;0.049510352;0.049209703;0.048830253;0.048366646;0.047812858;0.047162066;0.046406453;0.04553697;0.044543002;0.043411909;0.042128372;0.040673443;0.039023087;0.037145888;0.034999196;0.032522211;0.029622381;0.026144896;0.021789332;0.015782522;0;-0.015782522;-0.021789332;-0.026144896;-0.029622381;-0.032522211;-0.034999196;-0.037145888;-0.039023087;-0.040673443;-0.042128372;-0.043411909;-0.044543002;-0.04553697;-0.046406453;-0.047162066;-0.047812858;-0.048366646;-0.048830253;-0.049209703;-0.049510352;-0.049737002;-0.049893991;-0.049985255;-0.050014389;-0.049984688;-0.049899189;-0.049760699;-0.049571818;-0.049334968;-0.049052403;-0.048726231;-0.048358424;-0.047950828;-0.04750518;-0.047023106;-0.046506139;-0.045955718;-0.045373197;-0.04475985;-0.044116877;-0.043445402;-0.042746484;-0.042021117;-0.041270231;-0.040494697;-0.039695329;-0.038872887;-0.038028076;-0.037161548;-0.036273909;-0.035365713;-0.034437468;-0.033489635;-0.032522631;-0.031536828;-0.030532556;-0.029510101;-0.028469708;-0.027411581;-0.026335885;-0.025242745;-0.024132245;-0.023004432;-0.021859317;-0.020696868;-0.019517022;-0.018319675;-0.017104689;-0.015871888;-0.014621061;-0.013351962;-0.012064311;-0.010757789;-0.009432047;-0.008086699;-0.006721326;-0.005335474;-0.003928655;-0.002500348;-0.00105 + + + + + \ No newline at end of file diff --git a/schema/cpacs_schema.xsd b/schema/cpacs_schema.xsd index 7f09c96..6c9308e 100644 --- a/schema/cpacs_schema.xsd +++ b/schema/cpacs_schema.xsd @@ -1,40238 +1,40193 @@ - - - - - - - - - - - - - - - - - - - - CPACS root element - - - - - Version - - V3.5-beta - - Date - - 2023-08-06 - - - - 1. Overview - - - The - C - ommon - P - arametric - A - ircraft - C - onfiguration - S - cheme - (CPACS) - is an XML-based data format for describing aircraft configurations and their corresponding data. - - - This XMfL-Schema document ( - XSD - ) serves two purposes: (1) it defines the - CPACS - data structure used in the - XML - file (e.g., aircraft.xml) and - (2) it provides the corresponding documentation (see picture below). An XML processor (e.g., - - TiXI - https://github.com/DLR-SC/tixi - - or - XML tools in Eclipse) parses the XSD and XML files and validates whether the data set defined by the user (or tool) conforms to the given structure defined by the schema. - - - - - - This documentation explains the - elements - defined in - CPACS - and its corresponding - data types - . - Data types can either be - simple types - (string, double, boolean, etc.) or - complex types - (definition of attributes and sub-elements to build a hierarchical - structure). In addition, the sequence of the elements and their occurrence is documented. - - - To link the XML file to the XSD file, the header of the XML file should specify the path of the schema file. - An example could look like this: - - - ]]> - - - - CPACS is an open source project published by the - - German Aerospace Center (DLR e.V.) - https://www.dlr.de/ - - . For further information please visit - - www.cpacs.de - https://www.cpacs.de - - . - - - - - 2. Data structure - - - CPACS data is modeled in a hierarchical structure whose underlying concept follows a top-down description of a system-of-systems which decomposes a generic concept (e.g., an - aircraft - or - rotorcraft - ) into a more detailed description of its components. This originates from the conceptual and preliminary design of aircraft, where the level of detail is initially low and continues to increase as the design process progresses. - - - For some concepts within - CPACS - , however, a bottom-up approach is applied where the components are first defined in detail (sometimes referred to as - library - ) and then linked within an instantiated higher-level concept. This is advantageous when used multiple times within complex systems, such as - engines - , which only have to be defined once in order to be referenced several times on the - aircraft - . The combination of these two methodologies is known as middle-out approach and enables the goal to fully parametrize aeronautical systems. - - - - - - - - 3. Coordinate Systems - - - 3.1. CPACS coordinate system - - - Coordinate systems are a regular cause for ambiguous interpretation of data. In - CPACS - , the reference coordinate system is the - CPACS - -coordinate system. This coordinate system is used for most of the data. A single exception is made in order to keep aerodynamic data in an aerodynamic coordinate system. The following paragraphs outline the determination to known coordinate systems. - - - The - CPACS - coordinate system is the coordinate system identified by - - TiGL - https://dlr-sc.github.io/tigl - - , - CPACS - 's geometric library. It is a right-handed coordinate system. If an aircraft is defined in the - CPACS - coordinate system it will usually follow the directions listed in the table below. - - - Therefore, the - CPACS - coordinate system can be confused with the body-fixed coordinate system. While often the - CPACS - coordinate system and the body-fixed coordinate system overlap, this must not always be true. Several definitions for body-fixed coordinate systems exist (x-axis through nose and tail, x-axis perpendicular to nose plane). For non-symmetric aircraft, body-fixed coordinate systems become even more complicated. Hence, analysis tools should stick to the - CPACS - -Coordinate system. It remains to the designer to model the geometry accordingly. - - - The - CPACS - coordinate system does not rotate with flow. Hence, aerodynamic calculations do rotate their flow relative to the - CPACS - -coordinate system. If not stated explicitly different, e.g. for target lift-coefficients, results are returned in the - CPACS - coordinate system, i.e. the cfx-coefficient is parallel to the - CPACS - x-Coordinate, regardless of the way the geometry is defined. - - - The following table gives a "best-practice" advice on how to locate a geometry within - CPACS - . Different approaches are, of course, valid as well. - - - - - Axis - - - Direction - - - Description - - - - x - tailwards - from nose to tail - - - y - spanwise - from symmetry plane to the right wingtip - - - z - upwards - from landing gear to tip of vertical tailplane - - - - The following figures show an example of a geometry that is aligned with the - CPACS - coordinate system, i.e. the body-fixed coordinate system corresponds to the - CPACS - coordinate system. - - - - - - The aerodynamic analysis is relative to the - CPACS - coordinate system. That is, the angle of attack is represented by the dashed orange line. Results of the aerodynamic calculation are given in the - CPACS - coordinate system. - - - - - - The following figures give an example of a geometry that is not defined in alignment with the - CPACS - coordinate system. It is a valid - CPACS - file, but only used in this example for demonstrative purposes. - - - - - - The body axes and the - CPACS - coordinate system do not align. That is, the origin of the geometry is not at - CPACS - (0,0,0) but at a point in positive x- and z-direction. - - - - - - Again, the aerodynamic analysis is relative to the - CPACS - coordinate system. That is, the angle of attack is represented by the dashed orange line. Results of the aerodynamic calculation are given in the - CPACS - coordinate system. - - - 3.2. Local coordinate systems via parentUID and transformation - - - Some elements in - CPACS - , in particular the geometric components, are described in local coordinates. - The hierarchical data structure allows to define a local coordinate system either with respect to the coordinate system of the parent element or with respect to the global - CPACS - coordinate system. - This is achieved by combining the two elements - parentUID - and - transformation - : - - - - - parentUID - : An individual data hierarchy can be set up using the optional - parentUID - element. - Here it is - - important that exactly one element does not contain the - parentUID - - in order to identify the top element of this user-specific hierarchy. - As soon as the - parentUID - (which refers to the - uID - of the parent element) is set, a local coordinate system of the corresponding node is instantiated. - - - - - transformation - : This allows the coordinate system to be transformed via - translation - , - rotation - and - scaling - . - As soon as the - parentUID - is set, this transformation refers to the local coordinate system (in the current - CPACS - version this only affects - translation - ). - An attribute - refType - is used to either make this explicit ( - refType="absLocal" - ) or to override this and reference the global CPACS coordinate system instead ( - refType="absGlobal" - ). - - - - - The following table summarizes the possible combinations of - parentUID - and - transformation - and the resulting coordinate system (local or global): - - - - - - parentUID - not set - - - parentUID - set - - - - - transformation - without - refType - - global - local - - - - transformation - with - refType="absLocal" - - global - local - - - - transformation - with - refType="absGlobal" - - global - global - - - - Note: - The combination of - transformation - with - refType="absLocal" - and no - parentUID - is global, because the local coordinate system to which the transformation is referring to via - refType - equals the global coordinate system (see fuselage in the following example). - - - An exemplary use case further illustrates the concept of the coordinate system hierarchy. - The - CPACS - schema shall not specify in advance that a wing is always be part of the fuselage and engines must always be part of the wing. - In other cases the engine could be attached to the fuselage, which would not be possible via a predefined XML tree. - The following figure shows how components of the aircraft are related to each other via the - parentUID - . - The fairing is a child of the wing and is therefore automatically translated when the wing is translated. - Likewise, the horizontal tailplane is a part of the vertical tailplane and is therefore affected by translation of the latter: - - - - - - - - 4. Units - - - There are no explicit attributes describing units in - CPACS - . The general convention is that all values must be given in the following SI-units: - - - - [m] - Position, Distance - - - - [m - 2 - ] - - Area - - - - [m - 3 - ] - - Volume - - - [kg] - Mass - - - [s] - Time - - - [K] - Temperature - - - or in derived units, e.g.: - - - [N] - Force - - - [Nm] - Moment - - - [W] - Power - - - [J] - Energy - - - - The only non SI unit used throughout - CPACS - is the angle in degrees [°]. - For the sake of an intuitive use the angles are given in degrees rather than in radian [rad]. - - - - [°] - Angle - - - - - - - 5. Splitting up a - CPACS - dataset into several files - - - - To provide a better overview, it is possible to split up a - CPACS - dataset into several files. This can be done by inserting an - <externaldata> - node at an arbitrary position into the dataset. This node contains a - <path> - node with a URI to the external file(s), followed by one or more - <filename> - nodes, containing each a name of a file to be included at that position. Below, an example of such external data is given: - - - - - - - - - file:://airfoils - NACA0010.xml - NACA2412.xml - - - NACA 0012 Airfoil - ... - - - - - - ]]> - - - Such an external file would look like: - - - - NACA 0010 Airfoil - ... - - ]]> - - - The file would be included completely, except for its title line - <?xml version="1.0" encoding="utf-8"?> - . This concept can also be used recursively (external files of external files), but it is important to prevent circle connections (file "A" loading file "B" loading file "C" loading again file "A" ...). - - For path URI addresses, the trailing file separator "/" may be omitted. Below, some examples for path URIs are given: - - - Absolute local path: - file:///tmp - or - file:///c:/windows/tmp - - - Relative local directory: - file://relativeDirectory - or - file://../anotherRelativeDirectory - - - Remote net resource: - http://www.someurl.de - - - - With the help of the - Ti - XI - X - ML - I - nterface - - - TiXI - https://github.com/DLR-SC/tixi - - - , a - CPACS - dataset that is split into multiple files can be reassembled into a single tree structure for subsequent validation against the - CPACS - schema. The following commands are used to link external data sets: - - - - <externalFileName> - : Name of the external data file - - - <externalDataDirectory> - : Directory of the external data file. Its content is analogous to the - externaldata - 's - path - -element described above. - - - <externalDataNodePath> - : - - XPath - https://www.w3schools.com/xml/xpath_intro.asp - - of the node which is replaced with the content of the external file. In case that it is an external file of an external file, then it is the - XPath - in the outer external file. If, e.g., in the example above the - pointList - element would have also been loaded from an external file, then the entry would just be: - externalDataNodePath="/airfoil" - . This is used primarily for loop-detection. - - - The merged data tree for the example above would look like: - - - - - - - - NACA 0010 Airfoil - ... - - ... - - NACA 0012 Airfoil - ... - - - - - - ]]> - - - - - 6. UIDs and references - - - The - CPACS - -dataset often uses references between nodes. Typically, these - references define connections between elements which are located somewhere else in the hierarchical dataset (e.g. a - wing - is connected to a - fuselage - ; a specific - engine - is connected to a - pylon - ; etc.). These connections are defined by - unique identifiers - (uID) which are specified as attributes. Thus, there are elements which can be referenced via a - uID - attribute, e.g. a fuselage: - - ... - ]]> - - - - as well as elements which refer to the former, e.g. a wing pointing to its geometrical parent: - - - ATTAS main wing - ATTAS_fuselage - ... - ]]> - - - - In previous - CPACS - versions, referencing elements were identified via the - isLink="True" - attribute. Since this is superfluous due to the explicit definition of the element properties via the - CPACS - schema, this attribute no longer needs to be listed. It is nevertheless a valid optional attribute to ensure compatibility with older datasets, but might be removed in future versions. - - - Since - uID - s are only used to link nodes within the XML file, no naming convention is required. The characters only have to conform to the conventions of the - - xsd:ID - http://books.xmlschemata.org/relaxng/ch19-77151.html - - type standardized by the - - W3C - https://www.w3.org/ - - . - UIDs, however, must be unique! - Although a common practice for naming - uID - s is their position in the data hierarchy (e.g. - uID="mainWingSection3" - ), - uID - s as shown in the above example are absolutely valid as well. It is therefore recommended to use the - name - element - to convey human-readable meanings. - - - - - - 7. Usage of - name - , - description - and - uID - - - - CPACS is designed to serve as a central data exchange format in fully automated process chains. - A key requirement is therefore that tools can automatically read and process an incoming CPACS file. - A second requirement is that users can interpret the data set. - To address both requirements, the following usage of the - name - and - description - elements in combination with the - uID - attribute is proposed: - - - - - name - : A specification of the - name - element is usually mandatory for sequences of elements (e.g., if max occurrence is unbounded - [1..*] - ). - Typical examples are - wings/wing - , - aeroPerformance/aeroMap - or - missions/mission - . - Such elements must be able to be listed by tools, especially for visualization and reporting purposes, where the - name - element serves as a - concise and human-readable - indicator of the actual meaning of the corresponding element in the list (e.g., which - wing - , which - aeroMap - , which - mission - ). - This is usually a single word or a small number of words. - - - - - description - : This element is usually optional and is used to add - comprehensive and human-readable - explanations. This is usually at least one explanatory sentence. - - - - - uID - : As described in more detail in Section 6, the - uID - attribute is mainly used for internal referencing of CPACS elements. - Further processing software, e.g. - TiXI - and - TiGL - , also use the - uID - s to improve the robustness of the data query. - Consequently, the - uID - attribute serves as a - machine-readable - indicator and does not claim to be interpretable by human users. - In some practical use cases, the same string is chosen for - uID - and - name - . - However, restrictions on the choice of characters for the - uID - attribute must be considered, for example that no spaces may be used and the - uID - must be unique. - - - - - - Main wing - This is the main wing which was designed by my awesome wing sizing design tool. Your tool should not try to read and interpret what I'm writing here as typos are not recognized by XML processors. - - ]]> - - - - - 8. Symmetry - - - 8.1. Specification of symmetric elements - - - Sometimes it might be useful to specify a part of the aircraft as symmetric instead of holding all the data twice in nearly identical form in the dataset (e.g. left and right wing are usually identical, except for the sign of the y-coordinate). - Hence, some parts offer the option to set a - symmetry - attribute: - - - - ]]> - - - There are six possible attribute values: - - - x-y-plane - : Symmetry w.r.t. the x-y plane of the - CPACS - coordinate system - - - x-z-plane - : Symmetry w.r.t. the x-z plane of the - CPACS - coordinate system - - - y-z-plane - : Symmetry w.r.t. the y-z plane of the - CPACS - coordinate system - - - inherit - : Symmetry inherited from parent element (default behavior, i.e. also applies if attribute not set) - - - none - : Symmetry inheritance from parent element disabled - - - Note - : It must be taken from the documentation of the respective element which of these attribute values may be set. - - - One example of how to apply the - symmetry - attribute is shown in Sec. 3.2. Another simplified example shown below illustrates the combination of different symmetry properties of 4 wings: - - - - - - - Wing 1 - is mirrored on the x-z plane. - - - Wing 2 - has wing 1 as parent element, but suppresses its symmetry inheritance. - - - Wing 3 - has wing 2 as parent element and sets a new symmetry at the x-y plane. - - - Wing 4 - has wing 3 as parent element and no symmetry attribute specified. Thus, it inherits the symmetry at the x-y plane from wing 3. - - - - Note - : The corresponding transformations are not shown here. - - - 8.2. Referencing symmetric elements - - - All nodes (e.g., - parentUID - ) in - CPACS - that refer to a component holding the symmetry attribute (e.g., wing) might also have a - symmetry - attribute to specify how symmetry is propagated through the resulting element hierarchy. - - - The - symmetry - attribute of a referencing element may take three values: - symm - , - def - , - full - : - - - def: - The element refers to the geometric component that has a - symmetry - attribute and refers only to the defined side of the geometric component. - - - symm: - The element refers to the geometric component that has a - symmetry - attribute and refers only to the symmetric side of the geometric component. (Similar to the previous _symm solution) - - - full: - The element refers to the geometric component that has a - symmetry - attribute and refers to the complete component. (This is the default behaviour) - - - - - - - For example, to refer to the "other" side of a mirrored wing the following the following syntax might be used: - - - - wing - ]]> - - - Note: This feature is not implemented in TiGL. The upper figure is manually processed to illustrate the principle. In addition, there is an ongoing debate whether the approach is suitable for CPACS due to rapidly increasing complexity and unresolved implicit assumptions as to whether it is one or two components after mirroring. Therefore, it is advised to avoid using the symmetry attribute if possible. - - - - - 9. Vectors and arrays - - - For large data sets (e.g. increments of aerodynamic coefficients due to control surface deflections) it is advantageous - to map them via vectors and arrays instead of using a sequence of nodes for each data value. Therefore vectors and arrays are defined as semicolon-separated lists in - CPACS - . Via the documentation (derived from the XSD) of the corresponding nodes it has to be checked whether it is a vector or an array. - - - Vector - The vector is meant as a one-dimensional-array. In such a node, the values are given in a semicolon separated list: - - 0.;1.5;3.;4.5;6;7.5;9. - ]]> - - - - Array - - As for vectors, multi-dimensional arrays provide values in a semicolon separated list. An array is always preceded by a sequence of vectors, containing the dimensions and index values. Which vectors of an array are dimensioning is specified in the respective documentation of the array. - - - 1000.;2000.;3000. - - - InnerWingFlap - -1;-0.5;0;1 - - 11.;12.;13.;14.;21.;22.;23.;24.;31.;32.;33.;34. - ]]> - - - - Values for cl increments: - - - - Control parameter = -1 - Control parameter = -0.5 - Control parameter = 0 - Control parameter = 1 - - - Altitude = 1000m - 11. - 12. - 13. - 14. - - - Altitude = 2000m - 21. - 22. - 23. - 24. - - - Altitude = 3000m - 31. - 32. - 33. - 34. - - - - - - - - - - 10. Control Parameters - - Control parameters are abstract parameters, linking a generic floating point value to a certain status of a control device - (e.g. control surface, landing gear, suction system, brake parachute, ...). For control surfaces, such a data pair (control parameter - and control surface deflection status) is called a <step> and the ordered list of all steps for a control surface forms its deflection - <path>. - The control parameter values for each step are arbitrary floating point values. However, it is strongly recommended to use - values between -1. and +1., or between 0. And +1. (depending on the type of control surface). The smallest and the largest value implicitly - define the maximum deflection limits. It is mandatory, that the value “0.” is within the specified range, as this value is treated as - undeflected and used to specify a “clean” aircraft configuration (e.g. used in the clean aero performance map). It is recommended, but not - mandatory to specify a <step> with a <controlParameter> of 0. Consequently, no <controlParameter> must be used twice within - a single <path> definition. Deflection values between two specified steps are handled by linear interpolation. - The following example shows the usage of control parameters within a control surface deflection path definition: - - - - - ... - - ... - - - -1 - -20. - - - -0.5 - -10. - - - 0 - 0. - - - 1 - 5. - - - ... - ]]> - - - - - 11. Atmosphere - - - At some places in - CPACS - , an atmosphere has to be selected (e.g. for connecting an altitude with a certain pressure or density). - Currently, - CPACS - does only support a single atmospheric model: The ICAO Standard Atmosphere (ISA) from 1993 (see ICAO Doc 7488/3 'MANUAL OF THE ICAO STANDARD ATMOSPHERE', third edition, 1993) - It covers temperature, pressure, density, speed of sound, dynamic viscosity and kinematic viscosity with respect to altitude. - In - CPACS - , 'altitude' means what is called 'geopotential altitude' (H) in the ISA reference document and is given in [m]. - For details, see ISA manual, section 2.3, page E-viii f. - ISA covers a range from -5000 m to 80000 m. - - Temperature offsets are introduced on top of the definitions in the ISA manual (which does not cover such variations). The offset model - is based upon the idea that the pressure at a fixed geopotential altitude is independent from temperature offset (pressure altitude). - The temperature offset changes only the density (following rho = p / Gas Constant / T) (and viscosity, of course) - - - - CPACS 3.5-beta - - Release in August 2023 - - - new - headerType - and versioning strategy - - - cpacsVersion - marked as deprecated and moved to versionInfo node - - fix typos: - - various fixes in documentation - - airportCompatibility - - - mAdditionalCenterTanks - - - consistency - in - globalBeamPropertiesType - - - - capType - : add - uID - - - massBreakdown - - - - genericMassTyp - : add - componentUID - to link the corresponding components - - - mOperatorItemsType - : - - - - add - mAdditionalCenterTanks - - - add - mEngineAPUOils - - - add - mRemovableCrewRests - - - add - mToiletFluids - - - add - mUnusableFuels - - - add - mWaterReservoirs - - - add - mMiscellaneous - - - - align - mLandingGear - elements with more the new generic - landingGears - definition - - - - sparPositionType - : add - sparPositionCurve - (defines a spar position via a point on a curve) - - - isLink - attribute: marked as deprecated - - Systems definition - - - aeroMaps - - - - aeroLimitsIncrementMapType - : - controlDeviceUID - , ... --> - configurationDefinitionUID - - - aeroPerformanceBoundaryConditionsType - : - configurationType - --> - configurationDefinitionUID - - - aeroPerformanceIncrementMapType - : - controlDeviceUID - , ... -> - configurationDefinitionUIDs - - - - - - aircraftAnalysesType - - - - add - systemAnalyses - - - - - - aircraftModelType - - - - add - configurationDefinitions - - - add - systemArchitectures - - - - - - engineType - - - - add - rotors - - - - - - fuels - replaced by - chemicalEnergyCarriers - and - electricalEnergyCarriers - - - make sub-elements optional - - - - genericSystemType - : add - components - - - - operationalCaseType - - - - add - configurations - - - mPayload - optional - - - - - - vehiclesType - - - - add - systemElements - - - add - rotorElements - - - add - energyCarriers - - - - - - weightAndBalanceCaseType - - - - add - configurations - - - - - - aircraftModelType - - - - add - systemAnalyses/powerBreakdowns - - - - add cryogenic fuel storage - - add - ducts - definition - - hinge line definition aligned with TiGL - - fix wront type assignment in - costHydraulicSystemsType - - - wingWingAttachmentType - : - upperShellAttachment - and - lowerShellAttachment - restricted to - upperShell - and - lowerShell - - - add - wingCutouts - - - add - fuselageStructuralMountsType - - add CI schema validation - add python script for automatic syntax formatting - add automatic generation and publication of html documentation via GitHub actions and Appveyor - - - - - CPACS 3.4 - - Release in April 2022 - - - Revision of - decks - definition ( - compatibility break - ) - - - Mass breakdown: add - mSparSkins - and - mSparCells - to - mSpar - - - Mass breakdown: fix hierarchical error in - mMiscellaneous - ( - compatibility break - ) - - - Mass breakdown: fix typo in - mPylon - ( - compatibility break - ) - - - Nacelle guide curves: set - description - optional - - - Mission definition: add - uID - to elements in - geographicPointConstraintType - - - Mission definition: add - powerFraction - , - powerRemaining - and - powerConsumed - to - missionSegmentEndConditionType - - - Mission definition: rename - referenceEndCondition - to - referenceEndConditionUID - in - constraintSettingsType - ( - compatibility break - ) - - - Mission definition: rename - reqClassification - to - requirementClassification - in - flightPerformanceRequirementType - ( - compatibility break - ) - - Add contour coordinates for cell definition - Add vehicle independent node for external geometry - - Remove - paxFlow - element from - aircraftAnalysesType - ( - compatibility break - ) - - - Docs: improve documentation of - name - , - description - and - uID - usage - - - Docs: add description of - parentUID - concept - - Docs: add description of symmetry inheritance - Docs: add description of engine nacelles - Docs: add description of mission definition - General improvements of the documentation - - - - - CPACS 3.3 - - Release in June 2021 - - - Revision of the mission definition including parameter lapses within segments ( - compatibility break - ) - - - Revision of the point performance definition ( - compatibility break - ) - - - Revision of performance requirements ( - compatibility break - ) - - - Revision of landing gears ( - compatibility break - ) - - - Revision of control surface tracks definition ( - compatibility break - ) - - - Load analysis: Revision of flightLoadCasesType ( - compatibility break - ) - - - Load analysis: Revision of aeroCasesType ( - compatibility break - ) - - - Load analysis: loadEnvelopesType relocated and envelope simplified to a single uID-Sequence ( - compatibility break - ) - - - Load analysis: Replaced dynamicAircraftModel elements by loadApplicationPointSets ( - compatibility break - ) - - - Flight dynamics: Group flightPerformance, flyingQualities and trim under flightDynamics parent node ( - compatibility break - ) - - Introduced a configuration node to describe aircraft and payload configurations - Fuselage profiles: Introduced rectangle and super ellipse as standard profiles - Fuselage profiles: Added vector to specify curve parameters for profiles with kinks - Internal structure: Added standard profiles to profile based structural elements - Internal structure: Added ribPosts element to wingRibCrossSectionType - Internal structure: Upper and lowerCap now optional in sparCellType - Internal structure: Stringers and frames can reference sections - MassBreakdown: Set mass inertia Jxy, Jxz and Jyz optional - MassBreakdown: Added mMiscellaneous element - MassBreakdown: Added fuselage walls - Added flight envelope to aircraft global element - Added new base types: doubleVectorBaseType, posIntVectorBaseType, doubleArrayBaseType - Added 'none' and 'inherit' to list of symmetry flags - Set mapType attribute of vector and array elements to optional (requires TiXI>=3.1) - - AeroMaps: Defined angleOfSideslip as input and added distinction between minimum and maximum angleOfAttack in aeroLimitMaps ( - compatibility break - ) - - - AeroMaps: Added missing singular incrementMap element to incrementMaps in aeroLimitsMap ( - compatibility break - ) - - - AeroMaps: Adopted the camelCase style for damping derivatives ( - compatibility break - ) - - - Introduced common nomenclature for speeds and altitudes ( - compatibility break - ) - - Control distributors are set to optional - Added instructions for superposition of control surface deflections - Further elaboration of development standards - General improvements of the documentation - - - - - CPACS 3.2 - - Release in February 2020 - - Replaced tool-specific elements with xsd:any element and strict schema request for validation - UIDs adapted to type xsd:ID and xsd:IDREF - UIDs optional for transformationType and pointTypes - Replaced xsd:sequence elements with xsd:all elements where possible - CpacsVersion element set to optional - GuideCurves are now optional for nacelleCowlType - Documentation adaptions - - - - - CPACS 3.1 - - Release in August 2019 - - Redefinition of aeroPerformanceMaps - Added nodes for detailed engine pylons and nacelles - Added nodes to model generic walls - Extension of material definition - Added fuselage compartment definition - Added fuselage fuel tank definition - Explicit wing stringer definition integrated into wing stringer definition - RelativeDeflections renamed to control parameters - Control distributors modified to only have a single command input vector - "cpacsVersion" restricted to current schema version - Code cleanup - Cpacs_schema.xml removed - Documentation adaptions - - - - - CPACS 3.0 - - Release in Jul 2018 - - New component segment definition; this is affecting all structural components of wings - Renamed angleOfYaw into angleOfSideslip - Fixes in documentation - Made all uID attributes required - Minor fixes in choices and typos - Added nodes for the geometry of generic system components - Added performance requirements for aircraft models - Redefined the whole mission definition including point performances - Made link to missionUID in trajectory optional - Added new parameters to enginePerformanceMap - Relocated mFixedLeadingEdge and mFixedTrailingEdge within the massBReakdown structure - Changed aeroPerformanceMap to use altitude and standard atmosphere instead of reynolds number - Added an optional local direction for guide curves and an illustration image - Announced toolspecifics definitions as deprecated; will be removed from CPACS in next release and should be managed in separate namespace by tool maintainers - Added an option for aerodynamic performance maps of elastic aircraft - Enabled the definition of multiple aeroPerformanceMaps - Enabled the use of spar points for rib placement and rib points for spar placement - Added explicit stringer definitions for wing cells - All issues for this release can be found online - https://github.com/DLR-LY/CPACS/issues - - - - - CPACS 2.3.1 - - Release in Jul 2016 - - CPACS 2.3.1 is a beta release, all parameters may be subject to change. - Added a branch for the definition of design studies. - Added thermal properties for materials. - Revised the definition of flights/flightplans. - Added an airline definition. - Added structure for skid gear components. - Changed the units for material density to SI units. - Revised the top level fleets node and put it into the new airline node. - All issues for this release can be found online - https://github.com/DLR-LY/CPACS/issues - - - - - CPACS 2.3 - - Release in Nov 2015 - CPACS 2.3 is the fourth public release of CPACS. Major changes include: - - Included vector notation for weight and balance. - Included flight system and flight dynamic information. - Included top level aircraft requirements. - Included a prototype for detailed nacelle geometries. - Included structural mounts. - Extended aero data set for loads. - Extended the mass breakdown. - Updated the symmetry definition, please take a look at the documentation point 5 and 6. - All issues for this release can be found online - https://github.com/DLR-LY/CPACS/issues - - - - - CPACS 2.2.1 - - Release in Feb 2015 - - CPACS 2.2.1 is a beta release, all parameters may be subject to change. - Included preliminary definition of guidecurves. - Included additional means to describe the wing structure. - Included preliminary fuselage fuel tanks. - Included preliminary load envelope. - Included preliminary flight performance and flight qualities. (flight dynamics will follow) - Updated toolspecifics - Updated uncertainty definition - all issues can be found online - http://code.google.com/p/cpacs/issues/list - - - - - CPACS 2.2 - - Release in May 2014 - - CPACS 2.2 is the third public release of CPACS. Major changes include - Additions and changes to the loadCaseType. - Included additional genericGeometricEntities for bellyfairings etc. - The mass breakdown is extended for a more detailed fuselage structure. - Steadiness information on the geometry is excluded from CPACS 2.2. CPACS 2.3 will include optional guidelines for smoother surfaces. - Uncertainties can now be specified (CPACS 2.2alpha doubleBaseType, CPACS 2.2 also in vector notations) - all issues can be found online - http://code.google.com/p/cpacs/issues/list - - - - - CPACS 2.1 - - Release in May 2013 - - CPACS 2.1 is the second public release of CPACS. Most of the implementation was already included in CPACS 2.01 - included fuselage structure and cabin definition - all data is defined according to the CPACS coordinate system. That is the initial coordinate system in which geometries are defined. Therefore, it can but must not meet your body axis. - the mass breakdown is extended for a more detailed wing structure - profiles can now be included based on a two-dimensional class shape transformation. The old parametrization will still be available. TIGL will learn CST asap. - all issues can be found online - http://code.google.com/p/cpacs/issues/list - - - - - CPACS 2.01 - - Release in Nov 2012 - - CPACS 2.01 is an internal release for the VAMP project. It is the testbed for CPACS 2.1 - included fuselage structure - additions to the load case definition - all issues can be found online - http://code.google.com/p/cpacs/issues/list - - - - - CPACS 2.0 - - Release in Mar 2012 - - CPACS 2.0 is the first public release - large impacts on the documentation - all issues can be found online - http://code.google.com/p/cpacs/issues/list - compatible with TIGL 2.0 - excluded fuselage structure, reintegration in CPACS 2.1 - - - - - CPACS 1.6 - - Release in Jul 2011 - - Thanks for the input on the documentation to Felix Dorbath, Till Pfeiffer, Alexander Koch, Falk Heinecke and Tom Otten - preliminary added enginePylons - deleted seatAssemblyPositionType - updated toolspecific blocks from handbook aero and cpacs mass updater - added weight and balance definition - added loads reference axis and dynamic aircraft model - added wing documentation - added weights documentation - added fleet documentation - added paramam toolspecific documentation - added wing tank definition - changed some names in the massBreakdown - deleted old loadCaseDefinitions - no more plural element for loadAnalyses - shifted groundforces to groundloadcases, this will need an update - added noseLandingGear - mainLandingGear can now have plural SideStruts - - - - - CPACS 1.5 - - Release in Feb 2011 - - uID for transformation - extended stringUIDBaseType with optional attribute isLink - all elements xxxUID are now of Type stringUIDBaseType - added new material definition from FA to distinguish between different material types - changed fuselage structure definition due to input from BK - changed rib definition in cells in component segments - cleaned up material definition in component segments - added cpacsVersion information to the header and updates types - added area and length to the loadCase reference on wing strips - added wingFuselageAttachment - - - - - CPACS 1.4 - - Release in Nov 2010 - - Geometry definition for engine and nacelle added - Trailing Edge Devices, Leading Edge Devices and Spoilers added - Rotorcraft added, similar to aircraft - Splitted up multiple Point Types - sparCell added uID - new inline Documentation introduced in CPACS type - - - - - CPACS 1.3 - - Release in Aug 2010 - - Fuel definition added - Introduced component segments for the wing structure - Mission definition was updated - VSAero toolspecific data updated - - - - - CPACS 1.2 - - Release in May 2010 - - Fuselage Structure Elements are updated following the input from BK - - stringers>arbitrary additional parameters: yBezugAtStartX, zBezugAtStartX, yBezugAtEndX, zBezugAtEndX - paxCrossBeams additional parameters: startX, endX - cargoCrossBeams additional parameters: startX, endX - paxCrossBeamStruts additional parameters: startX, endX - cargoCrossBeamStruts additional parameters: startX, endX - structure>pressureBulkhead: positionX instead of positionZ - reinforcementNumberVertical: number of vertical reinforcements - reinforcementNumberHorizontal: number of horizontal reinforcements - maxFlectionDepth: max camber of pressure bulkhead - reinforcementNumber: number of reinforcements rear pressure bulkhead - sheetProperties: definition of sheet properties - innerRadius: inner radius of the pressure bulkhead - - Dummy Wingbox element is included. This definition needs further enhancements - - cpacs>vehicles>aircraft>model>fuselage>fuselage>structure - Wingbox: - xStart: start of the wingbox area - xEnd: end of the wingbox area - zStart: upper limit of the wingbox area - - Damping Derivatives are added in the form of dcfxdp, dcfxdq, dcfxdr, dcfydp, etc. The data will be stored in the model/global/aeroperformaneMap under a new dampingDerivatives element. Unit is deg/sec. - StructureProfiles are defined in the profiles element. They are referenced in structuralElements for several entities such as stringer, frame etc. Currently they are referenced via 'structuralProfileUID' for name consistency it should be either only 'structure' or only 'structural' - Control Commands. The chain between pilot inputs and controlsurface deflections is now closed. - - Parameters located at cpacs\vehicles\aircraft\model\systems - cockpitControl: links from pilotInput to commandCase - commandCase: links from commandCase to controlDistributor or controlFunction - controlDistributor links to the controlSurface - controlLaws includes controlModes automatic and manual - controlModes contain controlFunctions - - TraFuMo toolspecific data added - - - - - CPACS 1.1 - - Release in Feb 2010 - - Fleets model added. The fleets modeling from CATS is introduced to CPACS 1.1 - Reference changed. The reference type in wingSegmentStripCoefficientsType was changed from referenceType to pointType - - - - - - - - - - - - - - - - - - - - - - - - - Actuator attachment - - - - - - - - - - - - - Relative spanwise position of the actuator. - Eta refers to the dimensions of the control surface. - - - - - - - - - - - - - - - - Definition of the position and material properties of - the control surface actuator attachment. - - - - Definition of the position and material properties of - the control surface actuator attachment. - Please refer to the picture below for the definition - of the parameters: - - - - - - - - - - - - - - Definition of the relative chordwise position - of the parent actuator attachment. Xsi refers to the parents - dimensions. - - - - - Definition of the relative height position of - the parent actuator attachment. relHeight refers to the parents - dimensions. - - - - - Definition of the material properties of the - actuator attachment at the parent. - - - - - - - - - - - - - actuatorFuselageWingAttachmentType - - - - - - - - - - - - - - - - - - - - - - - actuatorFuselageWingType - - - - - - - - - - - - - Reference to the actuator. - - - - - Definition of the actuator to fuselage - attachment. - - - - - Definition of the actuator to wing attachment. - - - - - - - - - - - - - - - Definition of the position and material properties of - the parent actuator attachment. - - - - Definition of the position and material properties of - the parent actuator attachment. - Please refer to the picture below for the definition - of the parameters: - - - - - - - - - - - - - - Definition of the relative chordwise position - of the parent actuator attachment. Xsi refers to the parents - dimensions. - - - - - Definition of the relative height position of - the parent actuator attachment. relHeight refers to the parents - dimensions. - - - - - Definition of the material properties of the - actuator attachment at the parent. - - - - - - - - - - - - - actuatorsFuselageWingType - - - - - - - - - - - - - Definition of one actuator (e.g. trim actuator - of an HTP) of the attachment. - - - - - - - - - - - - - Aerodynamic loads - - - - Description of the aerodynamic loads - - - - - - - - - - - - Angle of attack [deg] - - - - - - - Angle of sideslip [deg] - - - - - - - - - - - - - - - - Aerodynamic coefficients - - - - A set of aerodynamic coefficients in the aerodynamic coordinate system - - - - - - - - - - - - Drag coefficient in aerodynamic - coordinates - - - - - - - Coefficient of the side force vector in - aerodynamic coordinates (perpendicular - to lift and drag) - - - - - - - Lift coefficient in aerodynamic - coordinates - - - - - - - Aerodynamic moment around d-axis of the aerodynamic coordinate system - - - - - - - Aerodynamic moment around s-axis of the aerodynamic coordinate system - - - - - - - Aerodynamic moment around l-axis of the aerodynamic coordinate system - - - - - - - - - - - - - - - Specification - - - - Specification of the vehicle properties and dynamics - - - - - - - - - - - Altitude - - - - - - - Mach number - - - - - - - Angle of sideslip [deg] - - - - - - - - Angle of attack [deg] - - - - - - - Target lift coefficient - - - - - - - - Normalized roll rate [rad/sec]. It is specified around the global x-axis - with the aircraft model's global reference point as origin and - nondimensionalized by: pStar = p * reference length / flow speed. - - - - - - - Normalized pitch rate [rad/sec]. It is specified around the global y-axis - with the aircraft model's global reference point as origin and - nondimensionalized by: qStar = q * reference length / flow speed. - - - - - - - Normalized yaw rate [rad/sec]. It is specified around the global z-axis - with the aircraft model's global reference point as origin and - nondimensionalized by: rStar = r * reference length / flow speed. - - - - - - - - Reference to a weight and balance description - - - - - - - - - - - - Aerodynamic load cases - - - - Combines a set of aerodynamic load cases - - - - - - - - - - - - - - - - - - - - Aerodynamic load case - - - - Specification of an aerodynamic load case - - - - - - - - - - - - Name - - - - - - - Description - - - - - - - - - - - - - - - - - Aerodynamic loads of components - - - - Specification of the aerodynamic loads of components - - - - - - - - - - - - - - - - - - - - Aerodynamic data of components - - - - Aerodynamic data of individual components of the aircraft (e.g. control surface loads and hinge moments) - - - - - - - - - - - - Reference to a component uID - - - - - - - - - - - - - - - Aerodynamic loads of the vehicle - - - - Description of the aerodynamic loads of the vehicle - - - - - - - - - - - - - - - - - - - - - aeroelasticDivergenceType - - - AeroelasticDivergence type, containing the results from - aeroelastic analysis - - - - - - - - - - - - - - - - - - - aeroelasticStaticMaxDisplacementType - - - AeroelasticStaticMaxDisplacement type, containing the - Maximum static displacement from aeroelastic analysis - - - - - - - - - - Maximum translation - - - - - Maximum rotation - - - - - - - - - - - - - Aeroelasticity - - - Aeroelastics type, containing the results from - aeroelastic analysis - - - - - - - - - - - - - - - - - - - - Increment maps for limitation values due to movable device deflections - - - Specification of aerodynamic coefficient increments due to movable device deflections (e.g., control - surfaces or landing gears). - - - - - - - - - - - - - - - - - - - Increment maps for limitation values due to movable device deflections - - - Specification of aerodynamic coefficient increments due to movable device deflections (e.g., control - surfaces or landing gears). - - - - - - - - - - - Configuration uID - - - - - Reference to an increment map of the aeroPerformanceMap - - - - - - Increments of the vehicle operation limits - - - - - - - - - - - - - - Aerodynamic limitations - - - - - This map explicitly specifies limitations of a vehicle in terms of angles of attack and sideslip angles. - All vectors, i.e. - altitude - , - machNumber - , - angleOfSideslip - and - angleOfAttack - , must have the - same length. To avoid redundancy with the - aeroPerformanceMap - , this type does not contain - any aerodynamic coefficients. - - - Since - angleOfSideslip - and - angleOfAttack - are closely interdependent for a given - machNumber - and - altitude - combination, a positive and negative maximum - angleOfAttack - is defined for a given combination of - machNumber - , - altitude - and - angleOfSideslip - . The limits of - angleOfSideslip - can be determined by evaluating the nominal decrease of - angleOfAttack - values or by - agreeint with the data supplier that the minimum and maximum value of the - angleOfSideslip - vector corresponds with physical limits. - - In order to avoid data redundancy, the operational limits should not reflect the extrema of aerodynamic - coefficients as these can be extracted from the performanceMap via interpolation. - - Note: - In future CPACS versions, a revision of the - aeroLimitsMap - will be targeted, since operational limits are not a purely aerodynamic issue. - - - - - - - - - - - - - Altitude [m] - - - - - - - Mach number - - - - - - - Angle of sideslip - - - - - - - - - - - - - - - - Vehicle operation limit - - - - Vehicle operation limit defined by sets of minimum and maximum - angleOfSideslip - and minimum and maximum - angleOfAttack - for a given altitude and Mach number. - This might be, e.g., a safety margin to the angle of attack at maximum lift or the flight - attitude a fighter aircraft is capable to fly in stalled conditions. The corresponding aerodynamic coefficients must - be extracted from the aeroPerformanceMap. - - - - - - - - - - - Minimum angle of attack defining the operation limit. Must be a vector of the same length as angleOfSideslip, machNumber and altitude. [deg] - - - - - Maximum angle of attack defining the operation limit. Must be a vector of the same length as angleOfSideslip, machNumber and altitude. [deg] - - - - - - - - - - - - - Aerodynamic map - - - - - The aeroMap contains aerodynamic coefficients and derivatives for a specific set of aerodynamic - and configurative boundary conditions. - - - The - aeroMap - allows for the simultaneous specification of multiple - controlDevice - settings. - In this case, it is assumed that a cumulative setting is built by summing up the individual settings. The correct - sequence of this summation is described in the - controlDistributorType - documentation. - - - - - - - - - - - - Name - - - - - Description - - - - - - - - - - - - - - - - - Boundary conditions - - - Specification of boundary conditions. - - - - - - - - - - - - Offset from temperature of the - atmospheric model [K]. For more details - on atmospheric models, please refer to - documentation of the <CPACS> root - element. - - - - - - - Configuration settings - - - - - - - - - - - - - - Increment maps for aerodynamic coefficients - - - - - - - - - - - - - - - - - - - Increment map from aerodynamic coefficients - - - The increment map is composed of two-dimensional arrays. The first dimension is given by the - length of the input vectors of the baseline aeroPerformanceMap and the second dimension by the vector of relative - deflections (or command inputs) of control surfaces (or control distributors). An example is described in the <CPACS> - root element. - - - - - - - - - - - - Reference to the uID of a control device, e.g. a control surface or a landing gear - - - - - Value of the command parameters of a control distributor. If not given explicitly in the control distributor, linear interpolation between the neighboring points is required. - - - - - - - Reference to a control distributor uID - - - - - Command inputs of a control distributor given as vector. If not given explicitly in the control distributor, linear interpolation between the neighboring points is required. - - - - - - - Increment of drag coefficient in aerodynamic coordinates - - - - - Increment of coefficient of the side force vector in aerodynamic coordinates (perpendicular to lift and drag) - - - - - Increment of lift coefficient in aerodynamic coordinates - - - - - Increment of cmd - - - - - Increment of cms - - - - - Increment of cml - - - - - - - - - - - - - - aeroPerformanceMapRCType - - - AeroPerformanceMapRC type, containing a performance map - with aerodynamic data. Array order is: angleOfAttack min->max - then angleOfSideslip then altitude then machNumber - - - - - - - - - - Atmospheric model and temperature offset - - - - - Mach number - - - - - Altitude - - - - - Sideslip angle - - - - - Angle of attack - - - - - Name and version of the tool used to compute - the aerodynamic performance - - - - - Modeling level of the methods used to compute - the aerodynamic performance. The higher the analysisLevel, the - higher the quality of the results. Possible use of - analysisLevel: 0- 9 = Statistical models, 10-19 = Analytic - models, 20-29 = Lifting line method, 30-39 = Panel method, 40-49 - = Panel-BL-coupled method, 50-59 = Full potential method, 60-69 - = Full potential-BL coupled method, 70-79 = CFD euler method, - 80-89 = CFD euler-bl coupled method, 99-99 = CFD RANS method, - >=100 = Experimental data. - - - - - - - - - - - - - - - - - - - - aeroPerformanceMapsRCType - - - aeroPerformanceMapsRC type, containing multiple - aeroPerformanceMapRC nodes for different cases - - - - - - - - - - - - - - - - - - - Aerodynamic coefficients and derivatives - - - - - Description - - - The aeroPerformanceMap contains a map - with aerodynamic data of the complete aircraft in the form of - nondimensional coefficients. The force coefficients in - i - -direction ( - ci - ) - are nondimensionalized by dynamic pressure and reference area, - the moment coefficients ( - cmi - ) by dynamic pressure, reference - area and reference length. - - All coefficients in the aeroPerformanceMap relate to - the aerodynamic coordinate system which is deducted from the CPACS coordinate system by - the transformations of angle of attack and angle of yaw. See the documentation of the - CPACS element for further details. - - - The dependent parameters of the aeroPerformanceMap are - altitude - , - machNumber - , - angleOfSideslip - and - angleOfAttack - . These elements are vectors of equal length, where values - with identical indices belong together. The solution vectors - ci - and - cmi - have the same length as the input vectors. Shown below is an example where - with 10 values per vector: - - <altitude mapType="vector">12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02</altitude> -<machNumber mapType="vector">0.2;0.2;0.2;0.2;0.2;0.2;0.2;0.2;0.2;0.2</machNumber> -<angleOfSideslip mapType="vector">0;0;0;0;0;2;2;2;2;2</angleOfSideslip> -<angleOfAttack mapType="vector">-2;0;2;4;6;-2;0;2;4;6</angleOfAttack> -<cd mapType="vector">0.056;0.094;0.132;0.17;0.208;0.072;0.11;0.148;0.186;0.224</cd> -<cs mapType="vector">0.;0.;0.;0.;0.;0.01;0.015;0.02;0.025;0.03</cs> -<cl mapType="vector">-0.1;0.04;0.18;0.32;0.46;-0.08;0.03;0.14;0.25;0.36</cl> - - - The aerodynamic coefficients for - altitude - =1200m, - machNumber - =0.2, - angleOfSideslip - =0° and - angleOfAttack - =6° can be found at the 5th index: - cd - =0.208, - cs - =0 and - cl - =0.46. - - - - - - - - - - - - - - - Altitude [m] - - - - - - - Mach number - - - - - - - Sideslip angle [deg] - - - - - - - Angle of attack [deg] - - - - - - - Drag coefficient in aerodynamic - coordinates - - - - - - - Coefficient of the side force vector in - aerodynamic coordinates (perpendicular - to lift and drag) - - - - - - - Lift coefficient in aerodynamic - coordinates - - - - - - - - - - - - - - - - - - - aeroPerformanceType - - - aeroPerformance type, containing performance maps with - aerodynamic data of an airfoil. - - - - - - - - - - Aerodynamic performance map of the full - configuration - - - - - Aerodynamic performance maps of isolated - fuselages - - - - - Aerodynamic performance maps of isolated wings - - - - - - Aerodynamic performance maps of control - surfaces - - - - - Aerodynamic performance maps of isolated - airfoils - - - - - - - - - - - - - Aerodynamic performance - - - - The aerodynamic coefficients and derivatives are stored in aerodynamic maps. Individual maps can be used to - gather the aerodynamic characteristics for specific boundary conditions. - - - - - - - - - - - - - - - - - - - - Global analysis information - - - - - - - - - - - - - - - - - - - - - - Results from several analysis - modules connected to CPACS - - - AircraftAnalyses type, containing detailed analysis - data of the aircraft - Within this element results from analysis modules are - stored that rely to the overall definition of the aircraft. These - include e.g. aerodynamic data or loadCases - For further documentation please refer to the - respective elements. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Control elements - - - Specification of control element settings. Control elements can be controlDistributors - or individual control devices, such as control surfaces or landing gears. - - - - - - - - - - - - - - - - - - - Control element - - - Specification of an control element setting. A control element can be a controlDistributor - or an individual control device, such as a control surface or a landing gear. - - - - - - - - - - - Reference to the uID of a control device, e.g. a control surface or a landing gear - - - - - Control parameter of the control device - - - - - - - Reference to a control distributor uID - - - - - Value of the command parameter of a control distributor. If not given explicitly in the control distributor, linear interpolation between the neighboring points is required. - - - - - - - - - - - - - - Global data - - - AircraftGlobal type, containing global data of the - aircraft - - - - - - - - - - - designRange equals the full payload max - range, i.e. point B in payload range - diagram - - - - - - - - - - - - - - - - - - Aircraft model - - - - - The - aircraftModelType - contains the geometric aircraft - model and associated data. - - - Elements specifying the geometry of the aircraft are - fuselages - , - wings - , - engines - (referenced via - uID - ), - enginePylons - , - landingGear - , - systems - (to some extend) and - genericGeometryComponents - . - - - Other elements are dedicated to additional data associated to this aircraft model. Brief and concise analysis results are stored - in the - global - node. The - analysis - node contains - extensive results from multidisciplinary analysis modules. - - - In the current CPACS version requirements only refer to the aircraft performance and are therefore specified in the - performanceRequirements - node. - - - - - - - - - - - - Name of the aircraft model - - - - - - Description of the aircraft model - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Aircraft - - - - - The - aircraftType - contains a list of aircraft models. - - - Note: Since there is no distinction between plural and singular in English, - aircraft - refers to plural form, while a single aircraft itself is referenced as - model - . - - - - - - - - - - - - - - - - - - - - - airfoilAeroPerformanceType - - - airfoilAeroPerformance type, containing performance maps - with aerodynamic data of an airfoil. - - - - - - - - - - Reference to the uID of the analysed airfoil - - - - - - References used for the calculation of the - force and moment coefficients of the airfoil (in the airfoil - axis system!) - - - - - Calculated aerodynamic performance maps of the - airfoil - - - - - - - - - - - - - airfoilsAeroPerformanceType - - - airfoilsAeroPerformance type, containing - airfoilsAeroPerformance - - - - - - - - - - - - - - - - - - - airframeMaintenanceCostType - - - - - - - - - - - - - - - - - - - - - - - Airlines - - - Contains a list of different airlines - - - - - - - - - - - - - - - - - - - airlineType - - - Describes a specific airline and their fleet - - - - - - - - - - Name of the airline - - - - - Description of the airline - - - - - - - - - - - - - - - Airport compatibility - - - - - - - - - - - - - - - - - - - - - - - - - - Airports - - - Airports type, containing data of the airports - - - - - - - - - - - - - - - - - - - - airportType - - - Airport type, containing data of an airport - - - - - - - - - - Name of airport - - - - - Description of airport - - - - - IATA 3-letter-code - - - - - ICAO 4-letter-code - - - - - Position in degrees north - - - - - Position in degrees east - - - - - Airport elevation - - - - - - - - - - - - - - - alignmentCrossBeamType - - - - - - - - - - - - - Offset in direction of extrusion, first side - (absolute value) - - - - - Offset in direction of extrusion, second side - (absolute value) - - - - - Rotation around local x axis (extrusion axis) - - - - - - Translation along local y axis (perpendicular - to extrusion axis) - - - - - Translation along local z axis (perpendicular - to x ynd y axes) - - - - - - - - - - - - - - alignmentFloorPanelType - - - - - - - - - - - - - Offset from seat rail 1 reference Position in - local y direction (in plane of panel, absolute value) - - - - - - Offset from seat rail 2 reference position in - local y direction (in plane of panel, absolute value) - - - - - - Offset from seat rail 1 reference position in - local z direction (in plane of panel, absolute value)) - - - - - - - - - - - - - - - alignmentStringFrameType - - - - - - - - - - - - - Rotation around local x axis (extrusion axis) - - - - - - Translation along local y axis (perpendicular - to extrusion axis) - - - - - Translation along local z axis (perpendicular - to x ynd y axes) - - - - - - - - - - - - - - alignmentStructMemberType - - - - - - - - - - - - - Offset in direction of extrusion (absolute - value) - - - - - Rotation around local x axis (extrusion axis) - - - - - - Translation along local y axis (perpendicular - to extrusion axis) - - - - - Translation along local z axis (perpendicular - to x ynd y axes) - - - - - - - - - - - - - - Alternating current - - - - - - - - - - - Effective voltage (also peak voltage) [V] - - - - - - - Frequency [Hz] - - - - - - - Frequency [Rad] - - - - - - - - - - - - - - Alternating current - - - - - - - - - - - Effective voltage (also peak voltage) [V] - - - - - - - Frequency [Hz] - - - - - - - Frequency [Rad] - - - - - - - - - - - - - - - Anisotropic material properties for 2D materials - - - - - Defines the material properties for a linear anisotropic material in the plane stress state (i.e., shell). The stress-strain relationship is defined as: - - - - The terminology of this complex type refers to the following literature: - - [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. - [2] J. N. Reddy, Mechanics of Laminated Composite Plates and Shells: Theory and Analysis, Second Edition. CRC Press, 2004. - - - - - - - - - - - - Coefficient 11 of reduced stiffness matrix [N/m^2] - - - - - Coefficient 12 of reduced stiffness matrix [N/m^2] - - - - - Coefficient 13 of reduced stiffness matrix [N/m^2] - - - - - Coefficient 22 of reduced stiffness matrix [N/m^2] - - - - - Coefficient 23 of reduced stiffness matrix [N/m^2] - - - - - Coefficient 33 of reduced stiffness matrix [N/m^2] - - - - - Thermal expansion coefficient in material direction - 1 [1/K] - - - - - Thermal expansion coefficient in material direction - 2 [1/K] - - - - - Thermal expansion coefficient in material direction - 12 [1/K] - - - - - Thermal conductivity of the material in material direction 1 [W/(m*K)] - - - - - - Thermal conductivity of the material in material direction 2 [W/(m*K)] - - - - - - Thermal conductivity of the material in material direction 3 [W/(m*K)] - - - - - - Allowable stress for tension in material direction 1 [N/m^2] - - - - - - Allowable stress for compression in material direction 1 [N/m^2] - - - - - - Allowable stress for tension in material direction 2 [N/m^2] - - - - - - Allowable stress for compression in material direction 2 [N/m^2] - - - - - - Allowable stress for shear [N/m^2] - - - - - - Allowable strain for tension in material direction 1 - - - - - Allowable strain for compression in material direction 1 - - - - - - Allowable strain for tension in material direction 2 - - - - - Allowable strain for compression in material direction 2 - - - - - - Allowable strain for shear - - - - - - - - - - - - - - Anisotropic material properties for 3D materials - - - - - Defines the material properties for a linear anisotropic material in three spatial directions (i.e., solid). The stress-strain relationship is defined as: - - - - The terminology of this complex type refers to the following literature: - - [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. - [2] J. N. Reddy, Mechanics of Laminated Composite Plates and Shells: Theory and Analysis, Second Edition. CRC Press, 2004. - - - - - - - - - - - - Coefficient 11 of stiffness matrix [N/m^2] - - - - - Coefficient 12 of stiffness matrix [N/m^2] - - - - - Coefficient 13 of stiffness matrix [N/m^2] - - - - - Coefficient 14 of stiffness matrix [N/m^2] - - - - - Coefficient 15 of stiffness matrix [N/m^2] - - - - - Coefficient 16 of stiffness matrix [N/m^2] - - - - - Coefficient 22 of stiffness matrix [N/m^2] - - - - - Coefficient 23 of stiffness matrix [N/m^2] - - - - - Coefficient 24 of stiffness matrix [N/m^2] - - - - - Coefficient 25 of stiffness matrix [N/m^2] - - - - - Coefficient 26 of stiffness matrix [N/m^2] - - - - - Coefficient 33 of stiffness matrix [N/m^2] - - - - - Coefficient 34 of stiffness matrix [N/m^2] - - - - - Coefficient 35 of stiffness matrix [N/m^2] - - - - - Coefficient 36 of stiffness matrix [N/m^2]2] - - - - - Coefficient 44 of stiffness matrix [N/m^2]] - - - - - Coefficient 45 of stiffness matrix [N/m^2] - - - - - Coefficient 46 of stiffness matrix [N/m^2] - - - - - Coefficient 55 of stiffness matrix [N/m^2] - - - - - Coefficient 56 of stiffness matrix [N/m^2] - - - - - Coefficient 66 of stiffness matrix [N/m^2] - - - - - Thermal expansion coefficient in material direction - 1 [1/K] - - - - - Thermal expansion coefficient in material direction - 2 [1/K] - - - - - Thermal expansion coefficient in material direction - 3 [1/K] - - - - - Thermal expansion coefficient affecting strain in material direction - 23 [1/K] - - - - - Thermal expansion coefficient affecting strain in material direction - 31 [1/K] - - - - - Thermal expansion coefficient affecting strain in material direction - 12 [1/K] - - - - - Thermal conductivity of the material in material direction 1 [W/(m*K)] - - - - - - Thermal conductivity of the material in material direction 2 [W/(m*K)] - - - - - - Thermal conductivity of the material in material direction 3 [W/(m*K)] - - - - - - Thermal conductivity of the material which couples heat flux in material direction 2 with temperature gradient in material direction 3 [W/(m*K)] - - - - - - Thermal conductivity of the material which couples heat flux in material direction 3 with temperature gradient in material direction 1 [W/(m*K)] - - - - - - Thermal conductivity of the material which couples heat flux in material direction 1 with temperature gradient in material direction 2 [W/(m*K)] - - - - - - Allowable stress for tension in material direction 1 - [N/m^2] - - - - - Allowable stress for compression in material - direction 1 [N/m^2] - - - - - Allowable stress for tension in material direction 2 - [N/m^2] - - - - - Allowable stress for compression in material - direction 2 [N/m^2] - - - - - Allowable stress for tension in material direction 3 - [N/m^2] - - - - - Allowable stress for compression in material - direction 3 [N/m^2] - - - - - Allowable stress for shear in 2-3 plane [N/m^2] - - - - - Allowable stress for shear in 3-1 plane [N/m^2] - - - - - - Allowable stress for shear in 1-2 plane [N/m^2] - - - - - Allowable strain for tension in material direction 1 - - - - - - Allowable strain for compression in material - direction 1 - - - - - Allowable strain for tension in material direction 2 - - - - - - Allowable strain for compression in material - direction 2 - - - - - Allowable strain for tension in material direction 3 - - - - - - Allowable strain for compression in material - direction 3 - - - - - Allowable strain for shear in 2-3 plane - - - - - - Allowable strain for shear in 3-1 plane - - - - - - Allowable strain for shear in 1-2 plane - - - - - - - - - - - - - - Category (ATA chapters) - - - - - - - - Environmental control - - - - - Auto flight - - - - - Communications - - - - - Electrical power - - - - - Equipment/furnishings - - - - - Fire protection - - - - - Flight controls - - - - - Fuel - - - - - Hydraulic power - - - - - Ice and rain protection - - - - - Landing gear - - - - - Lights - - - - - Water/waste - - - - - Cabin system - - - - - Cargo and accessory compartment - - - - - - - - - - - atmosphericModelType - - - Defines the the athmospheric model which should be used. - Currently there is only a single option which is ISA for ICAO Standard - atmosphere (ISA) from 1993. For more details on atmospheric - models, please refer to documentation of the <CPACS> root - element. - - - - - - - - - - Atmospheric model (e.g. ISA for ICAO Standard - atmosphere (ISA) from 1993). - - - - - - - - - - - - Offset from temperature of the atmospheric model [K]. - For more details on atmospheric models, please refer to documentation - of the <CPACS> root element. - - - - - - - - - - - - - Atmospheric model - - - Available options: ISA. See documentation of <CPACS> root element for further details. - - - - - - - - - - - - - - - - - - Definition of attachment pins for the wing-fuselage - attachment. - - - Definition of attachment pins for the wing-fuselage - attachment. - - - - - - - - - - - - - - - - - - - Attachment pin of the wing-fuselage-attachment. - - - - Attachment pin of the wing-fuselage-attachment. - - - - - - - - - - - - - Definition which translation degrees of - freedom are blocked. Default x=0 (free); y=1 (blocked); z=1 - (blocked). - - - - - - - - - - - - - - - - Bogie axle assemblies - - - - A list of axles that are attached to the bogie - and their relative position to it - - - - - - - - - - - - - - - - - - - - Bogie axle assembly - - - Description of an axle installed on the bogie and its - relative position to it - - - - - - - - - - - Relative position of the axle to the bogie (if more than one axle is defined; 0 = forward end of bogie; 1 = rear end of bogie) - - - - - - - - - - - - - - - - - - - Axle - - - Geometric description and material properties of the - landing gear axle - - - - - - - - - - Length of the axle. For a single wheel, the length is equal to the distance between the center of the piston and the center of the wheel. For two wheels, the length is equal to the distance between the centers of the wheels with the axis being centered w.r.t. to the Piston. - - - - - Axle shaft properties - - - - - Number of wheels attached to this axle - - - - - Defines the side of the first wheel (inboard or outboard; inboard corresponds to the negative y-direction or in flight direction left) for odd number of wheels on this axis. Each additional wheel is the added on the opposite site of the previous wheel. - - - - - - - - - - - - Properties of the wheel(s) attached to this axle. If more than one wheel is attached, all wheels on a single axis have the same properties. - - - - - - - - - - - - - - Batteries - - - - - - - - - - - - - - - - - - - Battery - - - - - - - - - - UID of an electric energy carrier - - - - - - - - - - - - - beamCrossSectionType - - - beamCrossSectionType, containing the beam geometrical - properties - - - - - - - - - - - - - - - - - - - - - - - - beamStiffnessType - - - globalBeamStiffnessType, containing the beam - stiffnesses such as EA, EI - - - - - - - - - - - - - - - - - - - - - - - - - - blockedDOFType - - - - - - - - - - - - - - - - - - - - - - - Bogie - - - Geometric description and material properties of the - landing gear axle bogie (including the axle configuration) - - - - - - - - - - Length of the bogie - - - - - Tilt angle of the bogie in airborne conditions - - - - - - - - - - - - - - - - booleanBaseType - - - Base type for boolean nodes (including external data - attributes) - - - - - - - - - - - - - - - - - - - Bounding Box - - - - - - - - - - Length in x - - - - - Length in y - - - - - Length in z - - - - - Origin - - - - - - - - - - - A list of uIDs referencing other structural/geometric - elements that shall serve as a boundary of the wall - element. Possible references are floor, wall or - genericGeometryComponent. A major requirement is that - the referenced element has an intersection with the wall - for at least the distance between two wall positions. So - that a full geometric face of the wall is bounded by it. - Neighbouring wall faces that are not completely bounded - by the reference element are not affected. - - - - - - - - - UID referencing another - structural/geometric element that shall - serve as a boundary of the wall element. - Possible references are floor, wall or - genericGeometryComponent. - - - - - - - - - - - - - - System breakdown data - - - - - - - - - - - - - - - - - - - System breakdown data - - - - - - - - - - - - - - - - - - - Cabin aisles - - - - - - - - - - - - - - - - - - - - - - Aisle - - - Aisles has as many entries as there are aisles in the - cabin. In a normal single aisle there are two aisles: the cabin - aisle and the aisle leading to the cockpit. - - - - - - - - - - Name - - - - - Description - - - - - Longitudinal coordinates. The - number of coordinates can be chosen as appropriate, the minimum - number is two. The coordinates are relative to the cabin origin. - - - - - - Center points of the aisle. The - y-vector has to have same length as the x-vector. The aisle - stretches equally left and right of the provided y-coordinate. - - - - - - Width of the aisle at floor level at each - y-coordinate - - - - - - - - - - - - - - Cabin geometry contours - - - Cabin geometry contour line collection type. By providing more than one entry, - a 3D cabin space can be described. - - - - - - - - - - - - - - - - - - - - Cabin geometry contour - - - Type to define a lateral position value "y" at a given height "z" (in the parent deck coordinate system) - for each entry "x" in the parent cabin geometry definition. - - - - - - - - - - - Vector with y-coordinates - - - - - Height z - - - - - - - - - - - - - Geometry - - - - - [ - WARNING: - This type is known to be susceptible to - inconsistencies and might therefore be removed in a future version of CPACS] - - - The geometry of the cabin roughly corresponds to the available design space in the cabin. - It is given in terms of constant height contour lines. - The lines all share a common - x - -vector. - The - y - vector provides the lateral - contour at Z-coordinate provided by the constant value - z - . - One or more contour lines can be given. - The cabin geometry is assumed to be symmetric. - - - - - - - - - - - - - - - Name - - - - - Description - - - - - - Vector of x coordinates - - - - - - - - - - - - - Cabin spaces - - - - - - - - - - - - - - - - - - - - - - Space - - - spaces describe areas in the cabin that need to be - clear for use as emergency area. Depending on the type of area, - it can have a height limit. The spaces are required for - downstream cabin design, for example to describe an empty cabin. - - - - - - - - - - - Name - - - - - Description - - - - - Vector with x-coordinates. These describe an area, so they - are not monotonous ascending. - - - - - Vector with y-coordinates at given x-coordinates. Warning: - x-y do not represent a function as single x-positions can have - multiple y-coordinates. Hence, no interpolation is possible. - - - - - - Height above the floor that is required to - be empty of any objects - - - - - - - - - - - - - - Cap - - - - SparCap type, containing the cross section area of the - spar cap and the material properties. - Please find below a picture where all spar cross - section parameters as well as the orientation references for - the material definition can be found: - - - - - - - - - - - - - - Area of the cap - - - - - - - - - - - - - - - Cargo container elements - - - Cargo container element collection type - - - - - - - - - - - - - - - - - - - Cargo container element for use in the decks - - - - - - - - - - - - - - - - - Description - - - - - - Contour: single or double - - - - - - - - - - - - - Delta x - - - - - - Delta y - - - - - - Delta y of the base - - - - - - Delta z - - - - - - Delta z kink - - - - - - - - - - - - - - - Cargo containers - - - Cargo container instance collection type. - - - - - - - - - - - - - - - - - - - Cargo container - - - Cargo container type for placing an instance of a cargo container in the parent deck. - - - - - - - - - - Name - - - - - Description - - - - - UID of the cargo container element in the cpacs/vehicles/deckElements node - - - - - Position in x - - - - - Position in y - - - - - - - - - - - - - - cargoCrossBeamsAssemblyType - - - CargoCrossBeamsAssembly type, containing cargo - crossBeam assemblies - - - - - - - - - - - - - - - - - - - cargoCrossBeamStrutsAssemblyType - - - CargoCrossBeamStrutsAssembly type, containing cargo - crossBeam strut assemblies - - - - - - - - - - - - - - - - - - - cargoDoorsAssemblyType - - - CargoDoorsAssembly type, containing cargo door - assemblies - - - - - - - - - - - - - - - - - - - Ceiling panel - - - Ceiling panel element collection type - - - - - - - - - - Ceiling panel element for use in the decks - - - - - - - - - - - - - Ceiling panels - - - Ceiling panel instance collection type. - - - - - - - - - - Ceiling panel - - - - - - - - - - - - - - Chordwise positioning of wing cells. - - - CellPositioningChordwise defines the chordwise direction of a wing cell either in two xsi - (xsi1 at innerBorder and xsi2 at outerBorder) coordinates, via referencing a spar-uID or via a - contour coordinate in chordwise direction. - - - - - - - - - - - Relative chordwise position of the inner end. - - - - - Relative chordwise position of the outer end. - - - - - - Reference to a spar as chordwise border. - - - - - Chordwise contour coordinate as chordwise border. 0 equals LE, 1 equals TE. - - - - - - - - - - - - - Spanwise positioning of wing cells. - - - CellPositioningSpanwise defines the chordwise direction of a wing cell either in two eta - (eta1 at leadingEdge and eta2 at trailingEdge) coordinates, via referencing a rib-uID or via a contour - coordinate in chordwise direction. - - - - - - - - - - - Relative spanwise position of the forward end. - - - - - Relative spanwise position of the rear end. - - - - - - - RibNumber is the reference to the rib number of the rib set which is referenced by 'ribDefinitionUID'. - - - - - Reference to a ribDefinition set. The single rib of this ribDefinition set is defined by using 'ribNumber'. - - - - - - Spanwise contour coordinate as spanwise border. 0 equals root, 1 equals tip. - - - - - - - - - - - - - centerFuselageAreasAssemblyType - - - centerFuselageAreasAssembly type, containing center - fuselage area assembly - - - - - - - - - - - - - - - - - - - centerFuselageAssemblyType - - - CenterFuselageAssembly type, containing wing box - assemblies - - - - - - - - - Choice between different center fuselage - modelling options - - - - Simplified center fuselage definition (rigid - body) - - - - UID of first frame in rigid center fuselage - area - - - - - UID of last frame in rigid center fuselage - area - - - - - UID of start stringer to define center - fuselage area - - - - - UID of end stringer to define center fuselage - area - - - - - - Detailed low wing center fuselage definition - (draft definition) - - - - - - Detailed high wing center fuselage definition - (draft definition) - - - - - - - - - - - - - - - centerFuselageHighWingConfiguration - - - - - - - - - - - - - - - - - - - - - - centerFuselageKeelbeamType - - - CenterFuselage / Keelbeam definition between mainframe1 - und mainframe3 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - centerFuselageLateralPanelsType - - - CenterFuselage / lateral Panel definition between - mainframe2 und mainframe3 - - - - - - - - - - - - - - - - - - - - - - - - - - centerFuselageLongFloorBeamConnectionType - - - CenterFuselage / Long. floor beam connection - - - - - - - - - - - - - - - - - - - - - centerFuselageLowWingConfiguration - - - - - - - - - - - - - - - - - - - - - - - - - centerFuselageMainFramesType - - - CenterFuselage / main frame definition, containing - mainframe and pressure Bulkhead definitions - - - - - - - - - - - - - - - - - - - - - - - - centerFuselagePressureFloorType - - - CenterFuselage / pressure floor definition between - mainframe2 und mainframe3 - - - - - - - - - - - - - - - - - - - - - - - - centerFuselagePressureFloorType - - - CenterFuselage / side box definition between mainframe2 - und mainframe3 - - - - - - - - - - - - - - - - - - - - - certificationCasesType - - - - - - - - - - - - - - - - - - - - - - Change log - - - - - - - - - - - - - - - - - - - chargesCostType - - - - - - - - - - - - - - - - - - - - - - - - - - Chemical energy carriers - - - - - - - - - - - - - - - - - - - Chemical energy carrier - - - - - - - - - - Name - - - - - Description - - - - - Type of energy carrier - - - - - - - - - - - - - Lower heating value - - - - - Density at 15deg C - - - - - CO2 emission index - - - - - H2O emission index - - - - - Energy specific cost - - - - - Freezing point - - - - - - - - - - - - - - Aerodynamic contributions of a chrordwise part within a wing segment strip - - - - Contains a list of chordwise parts within a wing segment strip for which aerodynamic coefficients are specified - - - - - - - - - - - - - - - - - - - - Aerodynamic contributions of a chordwise part within a within a wing segment strip - - - - - Describes the contributions of a specific par within a wing segment to the total aerodynamic coefficients of a wing segment strip - - - A - chordwisePart - aescribes the contributions of a specific chordwise part within a wing - strip - to the total aerodynamic coefficients of this - strip - . It extends spatially between the two - eta - positions of the parent - strip - (see - strip - documentation) and four - xsi - positions in the segment coordinate system. - As with the parent stips, only the trailing border ( - ..ToSegmentXsi - ) of a - chordwisePart - is defined, while the leading border always equals the trailing border of the preceding - chordwisePart - (or - 0 - for the first part). - To account for oblique trailing borders (e.g., to match the aileron on a tapered wing) two different - toSegmentXsi - positions can be defined, one at the inner border ( - innerBorderToSegmentXsi - ) and one at the outer border ( - innerBorderToSegmentXsi - ) of the parent strip. - The - innerBorderToSegmentXsi - and - outerBorderToSegmentXsi - of the last - chordwisePart - must be equal to 1. - - - - - - - - - - - - - Chordwise coordinate xsi in the segment coordinate system to define the end position of the chordwisePart at the inner eta border - - - - - - - Chordwise coordinate xsi in the segment coordinate system to define the end position of the chordwisePart at the outer eta border - - - - - - - - - - - - - - - - Class divider - - - Class divider element collection type - - - - - - - - - - Class divider element for use in the decks - - - - - - - - - - - - - Class dividers - - - Class divider instance collection type. - - - - - - - - - - Class divider - - - - - - - - - - - - - - cockpitControlsType - - - Cockpit controls type, containing the cockpit controls - - Some controls are mandatory, others can be added via - cockpitControl elements - - - - - - - - - - - - - - - - - - - - - - cockpitControlType - - - single cockpitControl is defined by a pilotInput and a - commandOutput. The commandOutput is linked to the commandCase - - - - - - - - - - - - - - - - - - - - - - - - - Reference values for aerodynamic coefficients - - - - Specification of reference values for aerodynamic coefficients. - - - - - - - - - - - - Reference area - - - - - - - Reference length - - - - - - - Reference point - - - - - - - Reference translation - - - - - - - Reference rotation - - - - - - - - - - - - - - Aerodynamic contributions of the components - - - - Contains a list of components for which aerodynamic coefficients are specified - - - - - - - - - - - - - - - - - - - - Aerodynamic contributions of a component - - - - Describes the contributions of a specific component to the total aerodynamic coefficients - - - - - - - - - - - - Reference to a component - - - - - - - - - - - - - - - Aerodynamic contributions of a wing segment - - - - - Describes the contributions of a specific wing segment to the total aerodynamic coefficients of a wing - - - It is obligatory to reference a segment via its - uID - and to provide its - coefficients - . The breakdown of the coefficients comprises the - strips - and - remainingContributions - . The latter must only be specified if - strips - is given. - - - - - - - - - - - - - Reference to a wing segment uID - - - - - - - - - - - - - - - - - - - Aerodynamic contributions of strips within a wing segment - - - - Contains a list of strips within a wing segment for which aerodynamic coefficients are specified - - - - - - - - - - - - - - - - - - - - Aerodynamic contributions of a strip within a wing segment - - - - - Describes the contributions of a specific strip within a wing segment to the total aerodynamic coefficients of a wing segment - - - The strip extends spatially between two - eta - coordinates (i.e., - from - an inner border - to - an outer border). - In order to avoid redundancy, the inner border (denoted as - from - ) is always identical to the outer border of the previous strip (denoted by - to - ). - Accordingly, only the - to - -border can be specified explicitly, while the - from - -border equals implicitly either to - 0 - (for the first strip) or the - toSegmentEta - value of the previous element. The - toSegmentEta - of the last - strip - must be equal to 1! - - - It is obligatory to provide the - coefficients - of the - strip - . The breakdown comprises the - chordwiseParts - and - remainingContributions - . The latter must only be specified if the breakdown into - chordwiseParts - is given. This breakdown is optional. If it is specified, but the sum of all chordwiseParts does not match the strip coefficients, one or more - remainingContributions - may be applied - to ensure consistency (sum of all - chordwiseParts - + sum of all - remainingContributions - must be equal to total strip coefficients). - - - - - - - - - - - - - Spanwise coordinate eta in the segment coordinate system to define the end of the strip - - - - - - - - - - - - - - - - - - - - Aerodynamic coefficients breakdown - - - - - Breakdown of the total aerodynamic coefficients into contributions - from the various vehicle componenents. A detailed breakdown is only specified - for the wing. Other components, such as the fuselage, are more generically - referred to as - otherComponents - . Since - the sum of the contributions within a breakdown must equal the total - coefficients, the remaining contributions must be listed in - remainingContributions - . - - - The - remainingContributions - cannot be defined alone. Either the - definition of a - wing - , - otherComponents - or both together is valid and can be combined with - remainingContributions - . - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Aerodynamic contributions of wing segments - - - - Contains a list of wing segments for which aerodynamic coefficients are specified - - - - - - - - - - - - - - - - - - - - Aerodynamic contributions of the wings - - - - Contains a list of wings for which aerodynamic coefficients are specified - - - - - - - - - - - - - - - - - - - - Aerodynamic contributions of a wing - - - - - Describes the contributions of a specific wing to the total aerodynamic coefficients of a vehicle - - - It is obligatory to reference a wing via its - uID - and to provide its - coefficients - . The breakdown of the coefficients comprises the - segments - and - remainingContributions - . The latter must only be specified if - segments - is given. - - - - - - - - - - - - - Reference to a wing uID - - - - - - - - - - - - - - - - - - - commandCaseCommandType - - - single commandCaseCommand can either hold a - controlFunction or a controlDistributor - - - - - - - - - - - - - - - - - - - - - - - commandCasesType - - - plural Element for commandCase, some fixed dp, dq, dr - and dx, dy, dz - - - - - - - - - - - - - - - - - - - - - - - - - commandCaseType - - - single commandCase Containing several - commandCaseCommands - - - - - - - - - - - - - - - - - - - - - - - - UIDs of 2d structural fuselage elements - (e.g., pressure bulkheads, walls or - floors). The compartment will be - enclosed with the fuselage skin - - - - - - - - - - - - - - - - - - The compartment defines an enclosed volume within the fuselage. It is defined by a set of border geometries. This could be pressureBulkheads, walls or floors and they are referred by their uIDs. The volume is closed with the fuselage skin. The geometry tool has to check, if the compartment definition gives a closed geometry. - - - - - - - - - - - The compartment defines an enclosed volume in the - fuselage. It is defined by a set of border geometries. - This could be pressureBulkheads, walls or floors and - they are referenced by their uIDs. The volume is closed - with the fuselage skin. The geometry tool has to check, - if the compartment definition gives a closed geometry. - - - - - - - - - Compartment geometry uIDs list. - - - - - - - Name of the compartment. - - - - - - - Description of the compartment. - - - - - - Ideal design volume of the compartment. - - - - - - - - - - - - - - - - - - - - - complexBaseType - - - Base type for complex nodes (including external data - attributes) - - - - - - - - - - - - - - - componentCostType - - - - - - - - - - - - - - - - - - - - - - componentSegmentPathType - - - - - - - - - - - - - Definition of hingePoint of the - componentSegment. The hingePoint is used as reference point for - the deflection definition. - - - - - Definition of the orientation of the hinge - line with three Euler-rotation angles. The hinge line is - oriented along the global y-axis if all rotations are 0. - - - - - - Definition of all steps of the deflection - path. - - - - - - - - - - - - - componentSegmentStepsType - - - - - - - - - - - - - Definition of one step of the deflection path. - - - - - - - - - - - - - - componentSegmentStepType - - - - - - - - - - - - - The control parameter is used to reference the - state of a control device, e.g. in the load - case description. Can have any value and is NOT limited to the - range of -1 to 1. - - - - - Translation along the x-, y- and z-Coordinate - of the rotated hinge coordinate system. - - - - - Rotation around the hinge line. - - - - - - - - - - - - - - ComponentSegments of the wing. - - - ComponentSegments type, containing all the - componentSegments of the wing. - - - - - - - - - - - - - - - - - - - ComponentSegment of the wing. - - - - Within componentSegments the wing structure, the - control surfaces, the wing fuel tanks and the - wingFuselageAttachment is defined by using relative coordinates. - - A componentSegment is defined in the same way as - segments: from one cross section (sections->elements) to - another. Compared to segments one componentSegment can can start - and end at elements that are not consecutive. Therefore that one - componentSegment can be the combination of several segments. - Each wing has at least one componentSegment (from root to tip). - The maximal number of componentSegments equals the number of - segments (each segment is defined as one componentSegment). - This also implies that each segment can only be part of one componentSegment. - - In principal a componentSegment can combine any number - of segments. But if in one section two elements are defined, the - componentSegment has to start/end there as no well-defined - relative coordinates can be defined if steps in the wing occur. - - An example for wing componentSegments can be found in - the picture below: - - - - Within componentSegments a relative spanwise - coordinate (eta) and a relative chordwise coordinate (xsi) is - defined. Those coordinates are used for the definition of e.g. - wing structures and control surfaces. there are two types of eta xsi coordinates. - Segment (eta, xsi) coordinates define the relative local coordinate system for a segment ranging from (0,0) to (1,1). - - - - - - The eta xsi coordinates for a component segment are based on the segment eta xsi planes. - As a reference length for the component segment eta coordinate the - mid chord lines of all the segments are used. - The beginning of this line at from-element equals eta = 0, while the end of this line - at the to-element equals eta = 1. All wing positions that lie on the same - element (segment border) have the same eta coordinate. The points in between - two elements are defined by the iso xsi lines of the segment eta xsi space. - An example for the definition of the relative axes can - be found in the picture below: - - - - - In order to calculate the global coordinates of a component segment eta xsi point - one first has to calculate the eta point on the xsi iso line of (xsi=0.5), - and then walk along the iso eta lineof the segment. - - An example for determining the a component - eta xsi point can be found in the picture below: - - - - - - - - - - - - - - - - - - - - - - - - Name of the wing componentSegment. - - - - - - - Description of the componentSegment. - - - - - - - Reference to the element from which the - componentSegment shall start. - - - - - - - Reference to the element from which the - componentSegment shall end. - - - - - - - - - Description of deflection path of - componentSegments (e.g. used for - trimmable HTPs). - - - - - - - - - - - - - - - - - - - Components - - - - - - - - - - - - - - - - - - - Component - - - - - - - - - - - Name - - - - - - - Description - - - - - - - - Link to pre-defined system element uID - - - - - - - Link to pre-defined system element uID - - - - - - - - - - - - - - - - - - compositeLayerType - - - CompositeLayer type, containing data of a composite - layer - - - - This type defines single composite layers by - giving a ply thickness, ply reference angle and a materialUID. - - - - - - - - Name of layer - - - - - Description of layer - - - - - Thickness of layer - - - - - Angle of layer in degree - - - - - Material UID of the layer - - - - - - - - - - - - - compositesType - - - - - - - - - - - - - - - - - - - - - - compositeType - - - Composite type, containing data of a composite - - - - - Within this type individual stackings of - composites can be introduced by defining an offset and a set of - composite layers. The order of the composite layers defines the - stacking order. - - - - - - - Name of composite - - - - - Description of composite - - - - - offset of the laminate. The reference plane of - the laminate is the arithmetic mean of the laminate thickness. - - - - - - - - - - - - - - - - Vehicle configurations - - - - List of vehicle configurations (e.g., setting of control surfaces, landing gear, etc.) - - - - - - - - - - - - - - - - - - - - Vehicle configuration - - - - - - - - - - - Name - - - - - - - Description - - - - - - - - - - - - - - - - - - - Configurations - - - - - - - - - - - - - - - - - - - - - - Configuration - - - - - - - - - - - - - UID of the configuration definition - - - - - Index of the weight and balance vectors to which the configuration applies to. [1;inf] - - - - - - - - - - - - - Configuration - - - - Contains references to control control devices and (or) the global aircraft configuration node. - - - - - - - - - - - - - Reference to the aircraft configuration definition node (aircraft/model/configurationDefinitions/configurationDefinition) - - - - - - - State description of the control elements - - - - - - - - - - - - - - connectivitiesType - - - - - - - - - - - - - - - - - - - - - - connectivityType - - - - - - - - - - - - - - - - - - - - - - - - - Constraint - - - - - Specification of performance constraints. - - - Constraints allow vectors of double values to define parameter lapses within a mission segment. The example below illustrates this by means of an exemplary climb profile of a conventional airliner, in which multiple physical and regulatory speed constraints are simultaneously specified over several altitudes (e.g., to account for the - crossover altitude - ): - - <endCondition> - <positionGeo> - <altitude relationalOperator="ge" uID="altClimb">10058.4</altitude> <!-- FL330 --> - </positionGeo> -</endCondition> -<constraint> - <referenceEndConditionUID>altClimb</referenceEndConditionUID> - <endConditionRatio>0.0;0.303</endConditionRatio> <!-- FL0, FL100 --> - <continuitySetting>discrete</continuitySetting> - <CAS relationalOperator="le">128.61;154.33</CAS> <!-- 250 [kt], 300 [kt]--> - <machNumber relationalOperator="le">0.78;0.78</machNumber> - <prioritySetting>velocity</prioritySetting> -</constraint> - - - From FL0 until FL100, the vehicle should fly at a velocity less than or equal to CAS = 250 kt or M = 0.78. In this first segment at low altitudes, the constraint on CAS is triggered. - - - From FL100 until FL330, the vehicle should fly at a velocity less than or equal to CAS = 300 kt or M = 0.78. In this second segment, the vehicle starts by increasing velocity until 300 kt, the constraint on maximum machNumber triggers from the crossover altitude onwards - - - - - - - - - - - - - Reference to the uID of the segment end condition variable to which a profile of constraintSettings is provided - - - - - - - Vector indicating the ratios of the constraintSettings profile with respect to the provided referenceEndCondition, ranging from 0 to 1. If this vector is defined, the provided constraintSettings are expected to be vectors with the same length providing ratio-value pairs. Example: for referenceEndCondition <range><z> (i.e.: flown distance in z direction of the segment), a vector of <CAS> and <machNumber> is provided to define a climb profile. - - - - - - Defines how to interpret the parameter lapses within the segment: discrete steps (C0 continuity) or linear interpolation (C1 continuity) - - - - - - - - - - - - - - - Calibrated airspeed within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Mach number within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Climb angle within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Rate of climb within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Specific excess power within the segment - (e.g.: for defining minimum SEP to - remain after step climbs have been - performed). - - - - - - - Altitude difference of each step climb - - - - - - - - Flight heading at the end of the segment in compassAngle with reference to true North [deg]. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Total change of heading angle during segment (a full turn is 360 degrees) [deg]. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - - Rate of turn within the segment [deg/s]. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Thrust setting for derated engine as fraction of max. Thrust (e.g.: for powered descents, deceleration not at IDLE, manoevres). If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Rate of velocity within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Load factor experienced during segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Constant altitude of the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - Priority setting indicating which constraint is preferred within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. - - - - - - - - - - - - - - - - - - - - - Mission segment constraints - - - Contains a set of constraints for the segment - - - - - - - - - - - - - - - - - - - Airfoil definition of an control surface at the - inner/outer border. - - - - Optional definition of the exact airfoil shape at the - inner/outer border of the control surface. - The airfoil shape is defined via referencing to the - airfoilUID. As the leading and trailing edge point is fix due to - the outer shape definition of the control surface the airfoil - can only be rotated around the x-axis (axis going from leading - to trailing edge of the inner/outer border of the control - surface). Scaling in x-direction is also defined by the outer - shape, wherefore only scaling in y and z direction is allowed. - - - - - - - - - - - - Reference to the airfoil uID. - - - - - - Rotation around an axis, going from the - leading edge point to the trailing edge point of the inner/outer - border of the control surface. Defaults to 90°, which is - equivalent to perpendicular on the control surface middle plane. - - - - - - Scaling of the airfoil in spanwise direction - (not used for 2D airfoils). - - - - - Scaling in thickness direction of the airfoil. - - - - - - - - - - - - - - controlDistributorsType - - - plural Element for controlDistributor - - - - - - - - - - - - - - - - - - - controlDistributorType - - - - single controlDistributor bundling several - controlElements - Within some analyses, it might occur that overlapping control element settings are specified. In this case, - it is assumed that a cumulative setting is built by summing up the individual settings. As the behavior of these settings - is not necessarily linear, a certain order of summation has to be followed: - - - The command inputs for each - controlDistributor - , coming from the - configurationUID - , as well as from separate settings have to be summed up to a total - commandInput - . - - - With this total - commandInput - , each corresponding - controlDistributor - definition has to be evaluated, in order to get - controlParameter - settings for a number of - controlDevices - . - - - All - controlParameter - settings for a - controlDevice - , coming from the - configurationUID - , from the - controlDistributors - and from separate - controlDevice - settings have to be summed up to get a total - controlParameter - for each controlDevice. - - - With this total - controlParameter - , each corresponding - controlDevice - definition has to be evaluated, in order to find out what the control device finally is doing. - - - During the summation process (depending on the order of processing within step 1 to 4), - commandInputs - or - controlParameters - might exceed the specified limits for that - controlDistributor - or - controlDevices - . As an intermediate result, this should be accepted – however, when it comes to evaluation in step 2 and 4, all - commandInputs - and - controlParameters - have to be within the specified limits. - - - - - - - - - - - - - - - Vector of command inputs. The minimum and maximum value is given by the lowest and highest entry of the vector, respectively. - - - - - - - - - - - - - - - controlElementsType - - - plural Element for controlElement - - - - - - - - - - - - - - - - - - - controlElementType - - - Single controlElement linking the inputs of a controlDistributor via a gain - table to a control device by using its uID. Controls can be ControlSurfaces and in the - future thrust. - - - - - - - - - - UID of the control device, e.g. a control surface. It is not allowed to reference another control distributor. - - - - - Vector of control device states resulting from the input commands. It must be of the same length as the inputCommands element. - The minimum and maximum values are defined according to the minimum and maximum values of the input commands. - - - - - - - - - - - - - controlFunctionsType - - - plural Element for controlFuntion - - - - - - - - - - - - - - - - - - - controlFunctionType - - - single controlFunction containing the controller's - parameters - - - - - - - - - - - - - - - - - - - - - - - - - - Controllability requirements - - - Contains a list of controllability requirements - - - - - - - - - - - - - - - - - - - - Controllability requirement - - - - - - - - - - Name - - - - - Description - - - - - UID of point performance definition - - - - - UID of weight and balance description - - - - - - - - - - - - - - - - controlLawModesType - - - Control Laws type, containing the aircraft's control - law modes - - - - - - - - - - - - - - - - - - - controlLawModeType - - - Control Laws type, containing the aircraft's control - law mode - - - - - - - - - - - - - - - - - - - controlLawsType - - - Control Laws type, containing the aircraft's control - laws - - - - - - - - - - - - - - - - - - - - Definition of actuators of the control surface, that - are not placed within a track. - - - Definition of actuators of the control surface, that - are not placed within a track. - - - - - - - - - - - - - - - - - - - Definition of an actuator of the control surface, that - is not placed within a track. - - - Definition of an actuator of the control surface, that - is not placed within a track. - - - - - - - - - - Reference to the actuator (actuator definition - currently not available in CPCAS, status 1.6). - - - - - - - - - - - - - - - - Airfoil definition of an control surface between inner - and outer border. - - - - Optional definition of the exact airfoil shape between - the inner and outer border of the control surface. - The airfoil shape is defined via referencing to the - airfoilUID. As the leading and trailing edge point is fix due to - the outer shape definition of the control surface the airfoil - can be rotated around the x-axis (axis going from leading to - trailing edge of the control surface) and around the z-axis - (normal axis on the control surface middle plane). Scaling in - x-direction is also defined by the outer shape, wherefore only - scaling in y and z direction is allowed. - - - - - - - - - - - Relative spanwise coordinate (eta) of the - control surface, where the leading edge of the airfoil is - placed. - - - - - Reference to the airfoil uID. - - - - - - Rotation around an axis, going from the - leading edge point to the trailing edge point of the control - surface. Defaults to 90°, which is equivalent to perpendicular - on the control surface middle plane. - - - - - Rotation of the airfoil around the control - surface middle plane normal direciotn. Reference point is the - most forward point of the airfoil. Defaults to 90°, which is - equivalent to the airfoilplacement in flight direction (along - wings-x axis). - - - - - Scaling of the airfoil in spanwise direction - (not used for 2D airfoils). - - - - - Scaling in thickness direction of the airfoil. - - - - - - - - - - - - - - Inner/outer border of the control surface. - - - - Definition of the inner/outer border of the control - surface. - The position on the planform of the control surface is - defined by defining the eta/xsi coordinates of the inner/outer - and forward/rear border. The eta/xsi coordinates refer to the - parent. - In addition, optionally, the airfoil shape of the - control surface can be defined closer. For the leading edge - devices 'hollow'. If an exact control surface airfoil definition - should be used, outerShape->airfoils can be used. - Please find below an example for the definition of the - planform of a trailing edge device. Other controlsurfaces are - similar. - - - - - - - - - - - - - - - - - Relative spanwise inner/outer position of the - leading edge of the control surface. - - - - - Relative spanwise inner/outer position of the - trailing edge of the control surface. Defaults to 'etaLE'. - - - - - - Relative chordwise inner/outer position of - the trailing edge of the control surface. Reference is eta/xsi - from the parent. - - - - - - - - - - - - - - - - - - - - - - - Inner/outer border of the control surface. - - - - Definition of the inner/outer border of the control - surface. - The position on the planform of the control surface is - defined by defining the eta/xsi coordinates of the inner/outer - and forward/rear border. The eta/xsi coordinates refer to the - parent. - In addition, optionally, the airfoil shape of the - control surface can be defined closer. For the - spoiler'relHeightLE' is used. If an exact control surface - airfoil definition should be used, outerShape->airfoils can - be used. - Please find below an example for the definition of the - planform of a trailing edge device. Other controlsurfaces are - similar. - - - - - - - - - - - - - - - - - Relative spanwise inner/outer position of the - leading edge of the control surface. Reference is eta/xsi from - the parent. - - - - - Relative spanwise inner/outer position of the - trailing edge of the control surface. Reference is eta/xsi from - the parent. Defaults to 'etaLE'. - - - - - Relative chordwise inner/outer position of the - leading edge of the control surface. Reference is eta/xsi from - the parent. - - - - - Relative chordwise inner/outer position of the - trailing edge of the control surface. Reference is eta/xsi from - the parent. - - - - - - Defines the relative high of lowest point of - the spoiler leading edge, relative to the airfoil height of the - parent at this position. See picture below. - - - - - - - - - - - - - - - - Inner/outer border of the control surface. - - - - Definition of the inner/outer border of the control - surface. - The position on the planform of the control surface is - defined by defining the eta/xsi coordinates of the inner/outer - and forward/rear border. The eta/xsi coordinates refer to the - parent. - In addition, optionally, the airfoil shape of the - control surface can be defined closer. For the trailing edge - device this is done at 'leadingEdgeShape', for the spoiler - 'relHeightLE' is used and for the leading edge devices 'hollow'. - If an exact control surface airfoil definition should be used, - outerShape->airfoils can be used. - Please find below an example for the definition of the - planform of a trailing edge device. Other controlsurfaces are - similar. - - - - - - - - - - - - - - - - - Relative spanwise inner/outer position of the - leading edge of the control surface. Reference is eta/xsi from - the parent. - - - - - Relative spanwise inner/outer position of the - trailing edge of the control surface. Reference is eta/xsi from - the parent. Defaults to 'etaLE'. - - - - - Relative chordwise inner/outer position of the - leading edge of the control surface. Reference is eta/xsi from - the parent. - - - - - - - - - - - - - - - - Optional definition of the exact airfoil shape of the - control surface. - - - - - - - - - - - - - - - - - - - - - - This type contains a list of control surfaces and their - deflection vectors - - - - - 0. General overview - - In this type, a list of control surfaces is defined. - - - - - - 1. - <controlSurface> - (mandatory) - - - One of these nodes per deflected control surface is - required here. - - - - - - - - - - - - - - - - - - - - - - This type contains a vector of deflection values for a - single control surface - - - - - 0. General overview - - In this type, a vector of deflections of a single - control surface is specified. - - - - - 1. - <controlSurfaceUID> - (mandatory) - - - A reference to a control surface from the aircraft - model - - - - - 2. - <controlParameters> - (mandatory) - - - A vector of controlParameters of the selected - control surface (with respect to the defined deflection path). - - - - - - - - - - - - - - Reference to a control surface - - - - - - Control parameters of the control surface - - - - - - - - - - - - - - controlSurfaceHingeMomentMapsType - - - controlSurfaceHingeMomentMapsType type, containing the - aerodynamic moment maps for one or more control surfaces. - - - - - - - - - - - - - - - - - - - - controlSurfaceHingeMomentMapType - - - controlSurfaceHingeMomentMap type, containing a moment - map with aerodynamic data for a control surface. Array order is: - controlParameters min->max then angleOfAttack then angleOfSideslip - then reynoldsNumber then machNumber. AngleOfAttack, angleOfSideslip, - reynoldsNumber and machNumber are taken from the basic - performance map one level above. - - - - - - - - - - Reference to the control surface - - - - - - Control parameters of the control surface - - - - - - - - - - - - - - - - - - - - controlSurfaceHingePointType - - - - The deflection path of a control surface is described - with respect to two hinge points - one at the inner border of - the control surface and one at the outer border of the control - surface. Those two points are defined using the xsi and relative - height coordinates of the parent. Therefore those points can also - lay outbound of the control surface. Those two points defined - the hinge line, which is a straight line between the two points. - - An example can be found below: - - - - - - - - - - - - - - Relative chordwise coordinate (xsi) of the - hinge line point. Reference is the parent chord. - - - - - - Relative height of the hinge line point. - Reference is the parent airfoil height. - - - - - Optional absolute translation of the hinge point. - This can be used to move the hinge points outside of the wing shape. - - - - - - - - - - - - - Outer shape definition of the control surface. - - - - - Definition of the outer shape of the leading edge - control surface. - The position on the planform of the control surface is - defined by defining the eta/xsi coordinates of the inner/outer - and forward/rear border. The eta/xsi coordinates refer to the - parent. - Please find below an example for the definition of the - planform of a trailing edge device. Other controlsurfaces are - similar. - - - - - - - - - - - - - - - - - - - - - - - - - Outer shape definition of the spoiler control surface. - - - - - Definition of the outer shape of the control surface. - - The position on the planform of the control surface is - defined by defining the eta/xsi coordinates of the inner/outer - and forward/rear border. The eta/xsi coordinates refer to the - parent. - Please find below an example for the definition of the - planform of a trailing edge device. Other controlsurfaces are - similar. - - - - - - - - - - - - - - - - - - - - - - - - - Outer shape definition of the control surface. - - - - - Definition of the outer shape of the trailing Edge - control surface. - The position on the planform of the control surface is - defined by defining the eta/xsi coordinates of the inner/outer - and forward/rear border. The eta/xsi coordinates refer to the - parent. - Please find below an example for the definition of the - planform of a trailing edge device. Other controlsurfaces are - similar. - - - - - - - - - - - - - - - - - - - - - - - - - Definition of the deflection path of the control - surface. - - - - The deflection path of a control surface is described - with respect to two hinge points - one at the inner border of - the control surface and one at the outer border of the control - surface. Those two points are defined using the xsi and relative - height coordinates of the parent. Therefore those points can also - lay outbound of the control surface. Those two points defined - the hinge line, which is a straight line between the two points. - - The deflection path of the control surface is defined - within the hinge line coordinat system. This is defined as - follows: The x-hinge coordinate equals the wing x-axis. The - y-hinge coordinate equals the hinge line axis (see above; - positive from inner to outer hinge point). The z-hinge line is - perpendicular on the x-hinge and y-hinge coordinate according to - the right hand rule. The rotation of the control surface is - defined as rotation around the positive y-hinge line. - - The deflection of the is defined in any number of - steps. The deflection of the control surface is done as follows: - First the x-deflection at the inner and outer border; afterwards - the z-deflection of the inner and outer border; last the - y-deflection of the inner border. The y-deflection is only - defined at the inner border, as it is identical to the outer - border. If no values for the outer border deflection are given, - they default to the values of the inner border. - An example can be found below: - - - - - - - - - - - - - - - - - - - - - - - - - controlSurfacePerformanceMapType - - - ControlSurfacePerformanceMap type, containing a delta - performance map with aerodynamic data for a control surface. Array - order is: relativeDeflection min->max then angleOfAttack then - angleOfSideslip then altitude then machNumber. AngleOfAttack, - angleOfSideslip, altitude and machNumber are taken from the - basic performance map one level above. - - - - - - - - - - Reference to the control surface - - - - - - Relative deflection of the control surface - - - - - - - - - - - - - - - - - - - - controlSurfacePerformanceMaps - - - controlSurfacePerformanceMaps type, containing the - aerodynamic delta performance maps for one or more control - surfaces. - - - - - - - - - - - - - - - - - - - Border type for the inner and outer border of a wing - cut out - - - - Maybe applied to specify inner and outer border of - the cutout either via eta or rib references - - - - - - - - - - - - - - - Link to a rib definition - - - - - - Rib number in the corresponding - ribDefinitionUID - - - - - - - Spanwise location of the border at the - leading edge of the cut out - - - - - Spanwise location of the border at the - trailing edge of the cut out - - - - - - - - - - - - - - Cut out of the parents upper/lower skin due to a - control surface. - - - - Optional. Definition of the skin cut out due to a - control surface. The cut out of the skin can either be defined - by referencing to a spar uID or by defining the relative chord - values (xsi) of the cut at the inner and outer border of the - control surface. The xsi value is based on the parents chord. - For leading edge devices additional parameters can be defined. - - An example for wing cut outs can be found in the - picture below: - - - - - - - - - - - - - - - Xsi value of the inner border, where the cut - out begins. - - - - - Xsi value of the outer border, where the cut - out begins. - - - - - - Reference to a spar, defining the skin cut - out. - - - - - - - - - - - - - Definition of the steps of the control surface - deflection path. - - - - List of steps. - - - - - - - - - - - - - - - - - - - - controlSurfaceStepType - - - - The deflection path of the control surface is defined - within the hinge line coordinat system. This is defined as - follows: The x-hinge coordinate equals the wing x-axis. The - y-hinge coordinate equals the hinge line axis (see above; - positive from inner to outer hinge point). The z-hinge line is - perpendicular on the x-hinge and y-hinge coordinate according to - the right hand rule. The rotation of the control surface is - defined as rotation around the positive y-hinge line. - - The deflection of the is defined in any number of - steps. The deflection of the control surface is done as follows: - First the x-deflection at the inner and outer border; afterwards - the z-deflection of the inner and outer border; last the - y-deflection of the inner border. The y-deflection is only - defined at the inner border, as it is identical to the outer - border. If no values for the outer border deflection are given, - they default to the values of the inner border. - An example can be found below: - - - - - - - - - - - - - - The control parameter links a generic floating point value to - a certain status of a control device (e.g. control surface, landing gear, suction - system, brake parachute, ...). See the documentation of the global CPACS-Element for - further information. - - - - - - Translation of the inner hinge line point - within the hinge line coordinate system. Defaults to zero. Not - allowed for spoilers! - - - - - Translation of the outer hinge line point - within the hinge line coordinate system. Defaults to the values - of the inner hinge line point. Not allowed for spoilers! - - - - - - Positive rotation around the hinge line, - heading from the inner to the outer border. Defaults to zero. - - - - - - - - - - - - - - controlSurfacesType - - - Definition of the outer shape, structure and deflection - of all control surfaces (flaps, slats, soiler, ailerons...) of - the wing. - - - - - - - - - - - - - - - - - - - - - Control surface tracks (mechnaical link between control - surface and parent). - - - - - - - - - - - - - - - - - - - - - - Control surface tracks (mechnaical link between control - surface and parent). - - - - - A - track - generally describes the structural connection between a control surface and a wing (or parent element). For example, a track can be a flap track, a revolute joint connecting an aileron or spoiler, or the kinematics of slats on a wing. - - - The spanwise position of the track is defined by - etaPosition - , which refers to the control surface dimensions. - - - The structural properties of the track (e.g. - materials) are defined in - trackStructure - . - - - If an actuator is included into the the track, a - reference is given in - actuator - . - - - The principal kinematic of the track is defined by - setting the - trackType - and - trackSubType - . Please refer to the - tables below for setting the - trackType - and - trackSubType - parameter. Note, those tables are not final - they are extended - continuously. - - - - - Trailing edge track types - - - trackType - picture - description - trackSubType - picture - description - - - 1 - - - - - - Revolute joint; no actuators; the revolute joint is on TED hinge line. - 1 - - - - - - Revolute attached at the wings rear spar and the TEDs front spar respectively the load - carrying ribs of the TED. - - - 2 - - - - - - Revolute joint; dropped hinge; linear or rotary actuator (subtype-dependent) included. - The drive strut (if any) is defined as strut1. - 1 - - - - - - Box beam design as wing attachment; rotary drive attached at wing rear spar. - - - - - - 2 - - - - - - Wing attachment at wing rear spar; rotary drive attached at wing rear spar - - - - - - 3 - - Track mounted inside the fuselage at wing root. - - - 3 - - - - - - Upside-down, forward link in conjunction with a straight track on a fixed structure - as aft. support; including rotary drive. - 1 - - - - - - Wing attachment using a box beam design where track is mounted; rotary actuator mounted - at the wing rear spar. - - - - - - 2 - - Track mounted inside the fuselage at wing root. - - - 4 - - - - - - Straight and sloped track on a fixed structure as forward support and an upright link as - aft. support; linear or rotary actuator (subtype-dependent) included. - 1 - - - - - - Wing attachment using a box beam design where the track is mounted; rotary actuator at - the wing rear spar. - - - - - - 2 - - - - - - Wing attachment using a box beam design where track is mounted; rotary actuator mounted - on the track. - - - - - - 3 - - Track mounted inside the fuselage at wing root. - - - - - - - - - - - - - - Relative chordwise position of the track. Eta - refers to the control surface. - - - - - Type of the track. Please refer to the remarks - of the controlSrufaceTrackTypeType for details. - - - - - - - - - - - - - - - - Type of the track. Please refer to the remarks - of the controlSrufaceTrackTypeType for details. - - - - - - - - - - - - - - - - - - - - - - - - - - Cut out of the parents structure due to a control - surface. - - - - Optional. Definition of the parents structure cut out - due to a control surface. The cut out is split into three parts: - cut out of the upper and lower skin and the definition of an - profile connecting the cut out of the upper and lower skin. - - An example for wing cut outs can be found in the - picture below: - - - - In the default configuration the cut out is as wide as - the control surface. If additional spacing is necessary inner - and outer border may be set. - - - - - - - - - - - - - - - - - - - - - - - - - costAirConditioningSystemsType - - - - - - - - - - - - - - - - - - - - - - - costAutomaticFlightSystemsType - - - - - - - - - - - - - - - - - - - - - - - costAuxilaryPowerUnitsType - - - - - - - - - - - - - - - - - - - - - - - costBleedAirSystemsType - - - - - - - - - - - - - - - - - - - - - - - costCommunicationSystemsType - - - - - - - - - - - - - - - - - - - - - - - costComponentsType - - - - - - - - - - - - - - - - - - - - - - - - - - costDeIcingSystemsType - - - - - - - - - - - - - - - - - - - - - - - costElectricalSystemsType - - - - - - - - - - - - - - - - - - - - - - - costEnginePylonsType - - - - - - - - - - - - - - - - - - - - - - - costEquippedEnginesType - - - - - - - - - - - - - - - - - - - - - - - costFireProtectionSystemsType - - - - - - - - - - - - - - - - - - - - - - - costFixedEmergencyOxygenSystemsType - - - - - - - - - - - - - - - - - - - - - - - costFlightControlSystemsType - - - - - - - - - - - - - - - - - - - - - - - costFuelSystemsType - - - - - - - - - - - - - - - - - - - - - - - costFurnishingElementsType - - - - - - - - - - - - - - - - - - - - - - - costFurnishingsType - - - - - - - - - - - - - - - - - - - - - - - - - - costFuselagesType - - - - - - - - - - - - - - - - - - - - - - - costHydraulicSystemsType - - - - - - - - - - - - - - - - - - - - - - - costInstrumentSystemsType - - - - - - - - - - - - - - - - - - - - - - - costLandingGearType - - - - - - - - - - - - - - - - - - - - - - - costLightingSystemsType - - - - - - - - - - - - - - - - - - - - - - - costNacellesType - - - - - - - - - - - - - - - - - - - - - - - costNavigationSystemsType - - - - - - - - - - - - - - - - - - - - - - - costPowerUnitsType - - - - - - - - - - - - - - - - - - - - - - - - - - costSystemsType - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - costWaterInstallationSystemsType - - - - - - - - - - - - - - - - - - - - - - - costWingsType - - - - - - - - - - - - - - - - - - - - - - - crashLoadCasesType - - - - - - - - - - - - - - - - - - - - - - crashLoadcaseType - - - CrashLoadcase type, containing a crash loadcase - - - - - - - - - - - - - Optional start of crash section: Default: - first frame of model - - - - - Optional end of crash section: Default: last - frame of model - - - - - Initial velocities - - - - - Initial rotations around axes, roll, pitch, - yaw - - - - - Initial rotational velocities around axes - - - - - - Definition of reference point to consider - rotation - - - - - AccelerationFields, usually gravity in z - - - - - - Definition of impact Surface for crash - simulation - - - - - - - - - - - - - - - - - - - - - - - crewCostType - - - - - - - - - - - - - - - - - - - - - - - - crossBeamAssemblyPositionType - - - CrossBeamAssemblyPosition type, containing the position - of a crossBeam assembly - - - - - - - - - - UID of profile based structural element to be - used as crossbeam - - - - - UID of the frame to which the crossbeam is - attached - - - - - Referenze z position of the crossbeam - - - - - - - - - - - - - - - - crossBeamStrutAssemblyPositionType - - - CrossBeamStrutAssemblyPosition type, containing a - crossBeam strut assembly position - - - - - - - - - - UID of profile based structural element to be - used as crossbeam strut - - - - - UID of the frame to which the crossbeam strut - is attached - - - - - UID of the crossbeam to which the crossbeam - strut is attached - - - - - Referenze y position of the strut at the - crossbeam intersection - - - - - angle of the strut in global yz plane - - - - - - - - - - - - - - - - cruiseRollersType - - - - - - - - - - - - - Definition of one cruise rollers/mid-span - stops. - - - - - - - - - - - - - cruiseRollerType - - - - - - - - - - - - - Definition of the position of the mid point of - the roll of the cruise roller. - - - - - Definition of the attachment of the cruise - roller to the parent of the flap. This is the track on which the - roll rolls during retracted flap position - - - - - Definition of the attachment of the cruise - roller to the flap. - - - - - Degree of freedom that is blocked by the - cruise roller if the flap is in retracted position. Positive = - cruise roller blocks bending in the direction of the upper skin - of the parent. Negative = cruise roller blocks bending in the - direction of the lower skin of the parent. - - - - - - - - - - - - - - cst2DType - - - - - - - - - - - A 2D implementation for Class shape - transformations. For more details look at AIAA Journal of Aircraft - Vol.45 No.1 2008 - - - - - The psi vector for definition of the class and - shape function, i.e. the points at which the CST functions will - be evaluated - - - - - N1 for the class function for the upper side - of the profile - - - - - N2 for the class function for the upper side - of the profile - - - - - B Coefficients for the Bernstein polynominal - on the upper side - - - - - N1 for the class function for the lower side - of the profile - - - - - N2 for the class function for the lower side - of the profile - - - - - B Coefficients for the Bernstein polynominal - on the lower side - - - - - Optionally, the trailingEdgeThickness of the - profile - - - - - - - - - - - - - Cuboid - - - A cuboid is defined with a default volume of 1m3. - - - - - - - - - - Length (default=1) [m] - - - - - Width (default=1) [m] - - - - - Height (default=1) [m] - - - - - - - - - - - - - Maps points (actually the index in the point list) to a curve parameter. - - - - Which parameters are allowed depends on the context. - For example in a wing profile, values between -1 and 1 are valid. - - - - - - - - - - - List of indices of points to be mapped. Each index must be in the range [1, npoints]. - - - - - List of parameters on the curve, that is mapped to the points defined by their index. - - - - - - - - - - - - - A curve that interpolates a list of points. - - - - The curve interpolates the list of points, typically with a b-spline. - In theory, the interpolation is somewhat ambiguous as it is not defined at which - curve parameter a point will be interpolated. - - To solve is ambiguity, an optional parameter map can be defined - that maps point indices with curve parameters. - - Kinks can also be modeled by populating the "kinks" array with the - indices of points that should be on a kink. As an example, look at the following image: - - - - - In this example, the kinks array will be "3;7". - Optionally, the parameters of the kinks can be set in the parameter map. - The whole profile looks as follows: - - -<pointList> - <x>...</x> - <y>...</y> - <z>...</z> - <kinks>3;7</kinks> - <parameterMap> - <pointIndex>3;5;7</pointIndex> - <paramOnCurve>0.2;0.5;0.8</paramOnCurve> - </parameterMap> -</pointList> - - - - - - - - - - - - Indices of points at which the curve has a kink. Each index is in the range [1, npoints]. - - - - - - Map between point index and curve parameter. - - - - - - - - - - - - - curvePointType - - - Point on a curve in normalized curve coordinates. - The referenceUID must reference a one-dimensional curve such as spars. - - - - - - - - - - Relative position on the referenced line/curve. - - - - - This reference uID determines the reference curve. - If it points to a spar, then the eta value is considered to be a spar coordinate - between start (eta=0) and end (eta=1) of the spar. - - - - - - - - - - - - - - - - - - - - - - - cutLoadIntegrationPointsType - - - cutLoadIntegrationPoints are defined in a vector - notation, due to the high amounts of data. Usually they well be - defined in between the ribs. Each point must have an id. - Optionally it is possible to rotate the orientation within a - cutloadIntegrationPoint to obtain meaningful results. The - orientation is optional and relative to the CPACS coordinate - system - - - - - - - - - - - - - - - - - - - - - - - - - cutOutControlPointsType - - - - - - - - - - - - - - - - - - - - - - - Additional definition of the leading edge cut out. - - - - - Optional. Definition of additional parameters, - describing the shape of the parents leading edge of the cut out - due to leading edge devices. - The parameters are described in the picture below: - - - - - - - - - - - - - - - Relative height of the most forward position of - the parents leading edge, relative to the airfoil height without - cut out. - - - - - Relative chordwise position of the most - forward position of the parents leading edge, relative to the - parents chord without cut out. - - - - - - - - - - - - - Definition of cut out profiles. - - - - - - - - - - - - - - - - - - - - - - - - Definition of cut out profiles. - - - - Optional, the exact shape between the upper and lower - skin cut out can be given by using cutOutProfiles. In general - cut out profiles are open profiles and not closed profiles as - e.g. wing airfoils. The placement, scaling and (partly) rotation - of the cut out profiles is fixed as the beginning and ending - point of the profile is fixed as can be seen in the two pictures - below. - - - - - - - - - - - - - - - - - Reference to the profile uID. Profiles should - be linked in profiles/structuralProfiles - - - - - Relative spanwise position of the cut out - profile. The eta coordinate refers to the control surface and - describes the cut out profile at the leading edge of the control - surface. - - - - - Rotation of the airfoil around the control - surface middle plane normal direciotn. Reference point is the - most forward point of the airfoil. Defaults to 90°, which is - equivalent to the airfoilplacement in flight direction (along - wings-x axis). - - - - - - - - - - - - - cutOutType - - - CutOut type, containing cut-outs - - - - - - - - - - Name of the cut out element - - - - - - Description of the cut out element - - - - - - Width of the cut element (absolute value) - - - - - - Height of the cut element (absolute value) - - - - - - Fillet radius of the cut element (absolute - value) - - - - - UID of a structural element that reinforces - the cut out - - - - - - - - - - - - - - Damping derivatives for positive and negative rotation - rates - - - - - 0. General overview - - This type contains the damping derivatives. They are - split up into those derivatives for positive rotation rates, - and those for negative rotation rates. - - - - 1. <positiveRates> (optional) - - Damping derivatives, calculated by positive rotation - rates. - - - - 2. <negativeRates> (optional) - - Damping derivatives, calculated by negative rotation - rates. - - - - - - - - - - - - - - - - - - - - - - - - Damping derivatives for positive and negative rotation rates - - - - - 0. General overview - - This type contains the damping derivatives. They are - split up into those derivatives for positive rotation rates, - and those for negative rotation rates. - - - - 1. <positiveRates> (optional) - - Damping derivatives, calculated by positive rotation - rates. - - - - 2. <negativeRates> (optional) - - Damping derivatives, calculated by negative rotation - rates. - - - - - - - - - - - - - - - - - - - - - - - Damping derivatives - - - This type contains aerodynamic performance maps with - the damping derivatives. The derivatives are calculated using - rotational rates [rad/s], normalized by: - Rate*ReferenceLength/flow speed. The rotations are performed - around the global axis directions with the aircraft model's - global reference point as origin. The damping derivative - performance maps are vectors of the same length as the input - vectors of the baseline aerodynamic performance maps, consisting of - semicolon separated values. - - - - - - - - - - - Change of cd by normalized roll rate - - - - - Change of cd by normalized pitch rate - - - - - Change of cd by normalized yaw rate - - - - - Change of cs by normalized roll rate - - - - - Change of cs by normalized pitch rate - - - - - Change of cs by normalized yaw rate - - - - - Change of cl by normalized roll rate - - - - - Change of cl by normalized pitch rate - - - - - Change of cl by normalized yaw rate - - - - - Change of cmd by normalized roll rate - - - - - Change of cmd by normalized pitch rate - - - - - Change of cmd by normalized yaw rate - - - - - Change of cms by normalized roll rate - - - - - Change of cms by normalized pitch rate - - - - - Change of cms by normalized yaw rate - - - - - Change of cml by normalized roll rate - - - - - Change of cml by normalized pitch rate - - - - - Change of cml by normalized yaw rate - - - - - - - - - - - - - damTolBehaviourType - - - - - - - - - - - - - Damage tolerance law, Walker approach - - - - - Damage tolerance law, Forman approach - - - - - - - - - - - - - damTolFormanType - - - - - - - - - - - - - Parameter Kc [Pa m^0.5] - - - - - Parameter C2 [m/cycle] - - - - - Parameter m2 [-] - - - - - - - - - - - - - damTolWalkerType - - - - - - - - - - - - - Fracture toughness KIc [Pa m^0.5] - - - - - Parameter C0 [m/cycle] - - - - - Parameter m [-] - - - - - Parameter gamma [-] - - - - - - - - - - - - - dateBaseType - - - Base type for date nodes (including external data attributes). - This date type is based on the xsd:date definition. - "To specify a time zone, you can either enter a date in UTC time by adding a "Z" behind the date - like this: 2002-09-24Z - or you can specify an offset from the UTC time by adding a positive or negative time behind the date - like this: - 2002-09-24-06:00 - or - 2002-09-24+06:00" (description taken from http://www.w3schools.com/xml/schema_dtypes_date.asp) - - - - - - - - - - - - - - - - - - - - dateTimeBaseType - - - Base type for dateTime nodes (including external data - attributes) - - - - - - - - - - - - - - - - - - - Deck component - - - - - - - - - - Name - - - - - Description - - - - - UID of the corresponding element in the cpacs/vehicles/deckElemets node - - - - - - - - - - - - - - - - Deck component - - - - - - - - - - Name - - - - - Description - - - - - UID of the corresponding element in the cpacs/vehicles/deckElemets node - - - - - - - - - - - - - - - - Deck doors - - - - - - - - - - - - - - - - - - - - - - Deck door - - - doors describe all doors of the cabin. They are linked - to a structural door description. The cabin door is usually equal - in size to the door, but does not need to be. The structural door - might describe a wider cut-out, while the cabin door is primarily - intended for evacuation modeling and cabin layout. In order to - obtain a 3-dimensional door representation, the local cabin - geometry shall be used. - - - - - - - - - - Name - - - - - Description - - - - - Number of passengers this door adds to the - overall exit capacity limit of the aircraft. - - - - - Opening geometry of the door - - - - - Door type (boarding, cargo, evacuation or service) - - - - - - - - - - - - - - - - - - - - - - - - Deck element - - - - - - - - - - Description - - - - - - - - - - - - - - - - Geometry - - - Description of the deck element geometry. This might be either a bounding box definition or a link to a generic geometry component. - - - - - - - - - - - - - - - - - - - - Mass - - - Description of mass, center of gravity and inertia - - - - - - - - - - - Mass value - - - - - Center of gravity (x,y,z) - - - - - - - - - - - - - - - Deck elements - - - A list of predefined elements which can be linked in the actual deck of the aircraft or rotorcraft model via referencing its uID. - - - - - - - - - - Ceiling panel elements for use in the decks - - - - - Class divider elements for use in the decks - - - - - Galley elements for use in the decks - - - - - Generic floor elements for use in the decks - - - - - Lavatory elements for use in the decks - - - - - Luggage compartment elements for use in the decks - - - - - Seat elements for use in the decks - - - - - Sidewall panel elements for use in the decks - - - - - Cargo container elements for use in the decks - - - - - - - - - - - - - Deck - - - Data of an aircraft or rotorcraft deck - - - - - - - - - - Name - - - - - Description - - - - - UID of the object used as parent coordinate system (typically the fuselage uID) - - - - - UID of the floor structure which supports this deck - - - - - The reference point of the deck/cabin. In a - conventional aircraft like the A320, it would be the rear wall - of the cockpit. The transformation is relative to the parent object - defined by “parentUID”, which should be the fuselage. - - - - - - Deck type: passanger, VIP, cargo or livestock - - - - - - - - - - - - - - - - Seat modules - - - - - Aisles - - - - - Spaces - - - - - Sidewall panels - - - - - Luggage compartments - - - - - Ceiling panels - - - - - Galleys - - - - - Generic floor modules - - - - - Lavatories - - - - - Class dividers - - - - - Cargo containers - - - - - Doors - - - - - - - - - - - - - - Structural mounts - - - Structural mount type containing the structural connections of cabin elements - - - - - - - - - - - - - - - - - - - Structural mount - - - Structural mount type containing the structural connections of cabin elements - - - - - - - - - - Name - - - - - Description - - - - - UID of the component to connect to - - - - - - - - - - - - - - Decks - - - List of decks - - - - - - - - - - - - - - - - - - - - deltaTemperatureType - - - - - - - - - - - - - - - - - - - - - - - - - - - - Design masses - - - The design mases are requerments which can com form the - TLARs - - - - - - - - - - Take off mass - - - - - Zero Fuel mass - - - - - Maximum landing mass - - - - - Maximum ramp mass (the maximum weight - authorised for the ground handling) - - - - - - - - - - - - - Design parameters list - - - Contains a list of all design parameters. - - - - - - - - - - - - - - - - - - - - Design parameter definition - - - Contains a the values of a parameter and its uid as reference. - - - - - - - - - - - - - - - - - - - - - - Design space definition - - - Contains the definition of the design space. - - - - - - - - - - - - - - - - - - - - - - - Design study definitions - - - Contains the data of design studies definitions. - - - - - - - - - - - - - - - - - - - - directOperatingCostType - - - - - - - - - - - - - - - - - - - - - - - - - - - - divergenceCasesType - - - DivergenceCases type, containing the cases for - aeroelastic divergence analysis - - - - - - - - - - - - - - - - - - - divergenceCaseType - - - DivergenceCase type, containing a case for aeroelastic - divergence analysis - - - - - - - - - - Mach number of divergence case - - - - - - Divergence stagnation pressure - - - - - - - - - - - - - - Dome Type - - - - - - - - - - - - - - - - - - - - - - - - - doorAssemblyPositionType - - - DoorAssemblyPosition type, containing the position of a door - assembly - - - - - - - - - - - - optional definition of door type (restricted to pax, - service, emergency, cargo) - - - - - - - - - - - - - - - UID of the door element - description - - - - - UID of the forward door frame - - - - - UID of the backward door frame - - - - - UID of the stringer at the upper door - edge - - - - - UID of the stringer at the lower door - edge - - - - - Lower height of the door with respect to the floor. - (Information necessary for boarding and evacuation analysis not - necessarily linked to structures) - - - - - Minimum widh of the door element. (Information - necessary for boarding and evacuation analysis not necessarily - linked to structures) - - - - - Minimum height of the door element. (Information - necessary for boarding and evacuation analysis not necessarily - linked to structures) - - - - - Door on right side of the fuselage = 1; on the left = - -1. (Information necessary for boarding and evacuation analysis not - necessarily linked to structures) - - - - - - - - - - - - - - doorCutOutType - - - CutOut type, containing cut-outs - - - - - - - - - - Name of door cutout element - - - - - Description of door cutout - element - - - - - Fillet radius of door cutout - element - - - - - Reference UID to the description of a DSS (door - surround structure) - - - - - - - - - - - - - - doorOpeningLegacyType - - - doors describe all doors of the cabin. They are linked - to a structural door description. The cabin door is usually equal - in size to the door, but does not need to be. The structural door - might describe a wider cut-out, while the cabin door is primarily - intended for evacuation modeling and cabin layout. In order to - obtain a 3-dimensional door representation, the local cabin - geometry shall be used. - - - - - - - - - - This is the forward x-coordinate of the door - relative to the cabin origin. - - - - - the door sill height relative to cabin origin. - - - - - - The width of the door in x-direction. - - - - - - the effective height of the door. - - - - - - - - - - - - - - - - - - - - - - - - "doorOpeningType" - - - Ceiling panel instance collection type. - - - - - - - - - - - - - - - - - - - - doorsType - - - Doors type, containing doors - - - - - - - - - - - - - - - - - - - doorSurroundStructurePositionType - - - DoorSurroundStructurePosition type, containing the position of a - door surround structure - - - - - - - - - - - - number of bays effected by DSS in front of - door - - - - - number of bays effected by DSS in behind of - door - - - - - number of bays effected by DSS - - - - - number of bays effected by DSS - - - - - - - - - - - - - - doorSurroundStructuresAssemblyType - - - doorSurroundStructuresAssembly type, containing - dorrSurroundStructure definitions - - - - - - - - - - - - - - - - - - - Array with semicolon separated values of type double - - - - - In - CPACS - arrays are used to exchange values - in full-factorial parameter spaces, for example to describe the aerodynamic coefficients depending - on Mach number and altitude. - - Thus, the dimensions of the array are spanned by the input vectors. See the following - example where two input vectors are defined. For clarification the entries of the array result from - the multiplication of the index values of the corresponding input vectors: - -<inputVector1>1;2;3</inputVector1> -<inputVector2>4;5;6;7</inputVector2> - - -<array>4;5;6;7;8;10;12;14;12;15;18;21</array> - - - Any entries of type - double - separated by semicolons are valid, e.g.: - - -<doubleArrayTest>123.456;+123.456;-1.234e56;-.45E-6;NaN;0</doubleArrayTest> - - -<doubleArrayTest>123.456</doubleArrayTest> - - -<doubleArrayTest>123.456,+1234.456</doubleArrayTest> - - -<doubleArrayTest>123.456;mainWingUID</doubleArrayTest> - - -<doubleArrayTest>1234.4E 56;-1.234e5.6</doubleArrayTest> - - - Please note that the syntax of arrays in the current - CPACS - version correspond exactly to the syntax of vectors. There is no special character indicating - the dimensions. Thus, the input vectors have to be determined from the documentation of the - corresponding elements and splitting of the one-dimensional vector has to be done manually. - - - - - - - - - - - - - - - - - - - doubleBaseType - - - - Base type for double nodes (including external data - attributes) - The double base type can include optional uncertainty - information. The description of uncertainties is placed in - additional attributes. First, it is described by an attribute - that describes the type of uncertainty function called - functionName. The functionName attribute includes the tag name - of the distribution function which is listened in the table - shown below. Each uncertainty function is further describes by a - set of parameters that are described in the table below. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - doubleConstraintBaseType - - - - Base type for double nodes including a relational operator attribute indicating valid constraint region - The doubleConstraintBaseType extends the doubleBaseType and thus inherits all its attributes. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Vector with semicolon separated values of type double - - - - - Any entries of type - double - separated by semicolons are permitted, e.g.: - - -<doubleVectorTest>123.456;+123.456;-1.234e56;-.45E-6;NaN</doubleVectorTest> - - -<doubleVectorTest>123.456</doubleVectorTest> - - -<doubleVectorTest>123.456,+1234.456</doubleVectorTest> - - -<doubleVectorTest>123.456;mainWingUID</doubleVectorTest> - - -<doubleVectorTest>123.456;1234.4E 56;-1.234e5.6</doubleVectorTest> - - - - - - - - - - - - - - - - - - - doubleVectorConstraintBaseType - - - - Base type for double vectors including a relational operator attribute indicating valid constraint region. - The doubleVectorConstraintBaseType extends the doubleVectorBaseType and thus inherits all its attributes. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Drag contributions - - - - The drag contributions relate to different physical mechanisms. The sum of the contributions does not have to be equal to the total drag. - - - - - - - - - - - - Drag contributions due to the displacement of the flow around a component. Zero for irrotational two-dimensional flows. - - - - - - - Drag contributions due to shear forces on surfaces - - - - - - - Drag contributions due to friction - - - - - - - Drag contributions due to energy loss through vortex structures caused by the pressure difference between the upper and lower sides of three-dimensional lifting surfaces. - - - - - - - Drag contributions due to mixing of streamlines between airframe components (e.g., interaction between wing and fuselage or pylon and wing). - - - - - - - Drag contributions due to energy dissipation in shock waves - - - - - - - Drag contributions due to trimmed aircraft configuration - - - - - - - - - - - - - - driveSystemsType - - - DriveSystems Type, containing all the drive systems - (combination of transmissions/gearboxes and shafts and their - links to engines and rotors) of a rotorcraft model. - - - - - - - - - - - - - - - - - - - driveSystemType - - - DriveSystem Type, defining a drive system (combination - of transmissions/gearboxes and shafts and their links to engines - and rotors) of a rotorcraft model. - - - - - - - - - - - - - - - - - - - - - Duct assembly - - - - - - - - - - - Name - - - - - - - Description - - - - - - - UID of part to which the duct is - mounted (if any) - - - - - - - - - - - - - - - - - - Duct structure - - - - - - - - - - - - - - - - - - - - - Ducts - - - - - - - - - - - - - - - - - - - - Duct - - - - - - - - - - - Name - - - - - - - Description - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - dynamicAircraftModelAnalysisType - - - - - - - - - - - - - - - - - - - - - - Electrical energy carriers - - - - - - - - - - - - - - - - - - - Electrical energy carrier - - - - - - - - - - Name - - - - - Description - - - - - Ratio of mass flow per energy flow - - - - - Specific energy - - - - - Density at 15deg C - - - - - Nominal C-Rate - - - - - Maximum C-Rate - - - - - - - - - - - - - - Electric motors - - - - - - - - - - - - - - - - - - - Electric motor - - - - - - - - - - - - - - - Electric power - - - - - - - - - - - Electric power values - - - - - - - - Direct current voltage [V] - - - - - - - - - - - - - - - - Electric power - - - - - - - - - - - Electric power value - - - - - - - - Direct current voltage [V] - - - - - - - - - - - - - - - - Ellipsoid dome - - - - - - - - - - Half axis fraction - - - - - - - - - - - - - Emissivity map, containing the diffuse emissivity of a material at different spectral lengths. - - - The emissivity of a material can vary with the spectral wave length. - The vectors diffuseEmissivity and waveLength must have the same size to be valid. - The data should be linearly interpolated. - - - - - - - - - - - Wave length in [m] - - - - - Diffuse emissivity of the material - - - - - - - - - - - - - Emtpy element - - - Base type for string nodes (including external data - attributes) - - - - - - - - - - - - - - - - - Energy Carriers - - - - - - - - - - - - - - - - - - - - Energy carrier (fuel) configuration - - - - - - - - - - - - - - - - - - - - engineAnalysisType - - - - - - - - - - - - - Thrust at takeoff - - - - - Fan pressure ratio at takeoff - - - - - - Bypass ratio at takeoff - - - - - overall pressure ratio at takeoff - - - - - - Maximum rotations per second, shaft 1 - - - - - - Maximum rotations per second, shaft 2 - - - - - - Design tip relative mach number (FAN) - - - - - - DryMass of engine - - - - - - - - - - - - - - Definition of global geometry parameters of the engine - fan. - - - - - - - - - - - - - Inner radius of the fan. - - - - - Outer radius of the fan. - - - - - - - - - - - - - Definition of the global engine geometry. - - - - All engine geometry definitions refer to the engine - coordinate system. The engine coordinate system has its orgine - in the middle of the fan plan. The positive x-axis is heading to - the rear, the positive z-axis to the top and the y-axis - according to the right hand rule. - - - - - - - - - - - length of engine - - - - - diameter of engine - - - - - dProp - - - - - Chordlength of a fan blade - - - - - - - - - - - - - - - - - engineGlobalType - - - EngineGlobal type, containing global engine data - - - - - - - - - - - Concept of engine - - - - - - - - - - - - - - - Year of first certification - - - - - - Rotation direction of the engine if looking at - it from the front, i.e. from propeller/fan to exhaust - - - - - - - - - - - - - - Hub to tip ratio - - - - - Number of rotor blades of fan - - - - - - Number of outlet guiding vanes - - - - - - Rotor stator spacing (relative to chordlength) - - - - - - - - - - - - - - List of all engine mounts. - - - - - - - - - - - - - - - - - - - - - - Definition of one engine mount. - - - - - - - - - - - - - Name of the engine mount. - - - - - Description of the engine mount. - - - - - - position of the engine mount referring to the - engine coordinate system. - - - - - - UID of the engine mount. - - - - - - - - - - - - Engine nacelle - - - - The engine nacelle is part of an engine. - It allows to define the outer geometry of the following engine components: - - Fan cowl - Core cowl - Center cowl - - - All geometric values refer to the fan position. - - - The common use case for this definition includes bypass engines. - In the case of non-bypass engines, the core cowl should be omitted. - - - - - - - - - - - - - - - Fan cowl - - - - - Core cowl - - - - - - - - - - - - - - - enginePerformanceMapsType - - - - - - - - - - - - - - - - - - - - - - enginePerformanceMapType - - - EnginePerformanceMap type, containing a performance map - with engine data - - - - - - - - - - - - - - Flight Level - - - - - Mach number - - - - - Absolute thrust [N] - - - - - Fuel mass flow - - - - - Speed at core engine nozzle - - - - - - Total temperature at core engine nozzle - - - - - - Mass flow through core engine nozzle - - - - - - Speed at bypass nozzle - - - - - Total temperature at bypass nozzle - - - - - - Mass flow through bypass nozzle - - - - - - Percent of n1Max, shaft 1 - - - - - Percent of n2Max, shaft 2 - - - - - Fan pressure ratio - - - - - Fan efficiency - - - - - Turbine entry total temperature - - - - - - Emission index Carbon Monoxide - - - - - - Emission index Nitrogen Oxide - - - - - - Emission index Sulfur Oxide - - - - - - Emission index Soot - - - - - Emission index unburned hydrocarbon - - - - - - air density at core outlet 8 - - - - - - air density at bypass outlet 18 - - - - - - area at core outlet - - - - - area at bypass outlet - - - - - - - - - - - - - - Engine references - - - EnginePositions type, containing a reference to the - used engines and their positions at the configuration - - - - - - - - - - - - - - - - - - - enginePositionType - - - EnginePosition type, containing data for a single - engine - - - - - - - - - - Name of the engine - - - - - Description of the engine - - - - - Reference to the used engine - - - - - - Component, to which the engine is mounted - - - - - - - - - - - - - - - - - Engine pylons - - - - - - - - - - - - - - - - - - - - - - Definition of one engine pylon. - - - - - - - - - - - - - Name of the engine pylon. - - - - - Description of the engine pylon. - - - - - - UID of the parent (normally wing or fuselage). - - - - - - - - - - - - UID of the engine pylon. - - - - - - - - - - - - - Rotors - - - - - - - - - - - - - - - - - - - - Propeller - - - - - - - - - - - - - - - - - - - - - - Definition of the engine spinner geometry. - - - - - - - - - - - - - Most forward x-position of the spinner. - - - - - - X-position of the spinner base. - - - - - - Radius of the spinner at the base position. - - - - - - - - - - - - - - Engines - - - Engines type, containing complete engine configurations - - - - - - - - - - - - - - - - - - - - engineType - - - Engine type, containing engine data. - - - - - - - - - - Name of engine - - - - - Description of engine - - - - - Scaling of engine take-off thrust - - - - - - - - - - - - - - - - - - - - - Environmental conditions - - - - Specification of environmental conditions - - - - - - - - - - - - Delta temperature with respect to the standard temperature of the selected atmosphere [K] - - - - - - - - - - - - - - etaIsoLineType - - - Iso line described by point of the same eta coordinate. - Can be either segment or component segment coordinates. - - - - - - - - - - Relative spanwise position. Eta refers to the segment or componentSegment depending on the referenced uID. - - - - - This reference uID determines the reference coordinate system. - If it points to a segment, then the eta value is considered to be in segment - eta coordinate; if it points to a componentSegment, - then componentSegment eta coordinate is used. - - - - - - - - - - - - - Point in eta and xsi coordinates - - - Point described by eta-xsi coordinates. - Can be either segment or component segment coordinates. - - - - - - - - - - Relative spanwise position. Eta refers to the segment or componentSegment depending on the referenced uID. - - - - - Relative chordwise position. Xsi refers to the segment or componentSegment depending on the referenced uID. - - - - - This reference uID determines the reference coordinate system. - If it points to a segment, then the eta-xsi values are considered to be in segment - eta-xsi coordinates; if it points to a componentSegment, - then componentSegment eta-xsi coordinates are used. - - - - - - - - - - - - - Relative height at eta, xsi position - - - Point described by eta-xsi and a relative height coordinate. - Can be either segment or component segment coordinates. - If relHeight is not given, the point has no offset from the eta-xsi plane - - - - - - - - - - Relative spanwise position. Eta refers to the segment or componentSegment depending on the referenced uID. - - - - - Relative chordwise position. Xsi refers to the segment or componentSegment depending on the referenced uID. - - - - - Relative height position. - relHeight is relative to the local airfoil thickness. - - - - - This reference uID determines the reference coordinate system. - If it points to a segment, then the eta-xsi values are considered to be in segment - eta-xsi coordinates; if it points to a componentSegment, - then componentSegment eta-xsi coordinates are used. - - - - - - - - - - - - - fatigueBehaviourType - - - - - - - - - - - - - Fatigue law, stress based Brown Miller approach [N/m^2] - - - - - - - - - - - - - fatigueStressBasedBrownMillerType - - - - - - - - - - - - - Parameter sigma_f [N/m^2] - - - - - Parameter b [-] - - - - - Parameter epsilon_f [-] - - - - - Parameter c [-] - - - - - - - - - - - - - fleetType - - - Each fleet can be divided into sub fleet groups - - - - - - - - - - Name of fleet - - - - - Description of the fleet - - - - - Description of sub-fleets. - - - - - - - - - - - - - - flightAnalysisType - - - - - - - - - - - - - - - - - - - - - - - Flight dynamics - - - - - - - - - - - - - - - - - - - - - - - - Linear model parameters - - - - - - - - - - - - - - - - - - - - - - - - - - Trim result - - - - - - - - - - - Mach number - - - - - - - True airspeed - - - - - - - Angle of attack - - - - - - - Altitude - - - - - - - - - - - - - - Flight envelope speed - - - - Specification of the V-speed - - - - - - - - - - - - - Vector with altitudes - - - - - - - Vector with True Airspeeds - - - - - - - - - - - - - - Flight Envelopes - - - - Specification of flight envelopes - - - - - - - - - - - - - - - - - - - - Flight Envelope - - - - Specification of a flight envelope - - - - - - - - - - - - Offset from temperature of the atmospheric model [K] - - - - - - - - - - - - - - - Flight load cases - - - - - - - - - - - - - - - - - - - - - - Load conditions - - - Inertia load conditions acting on the aircraft - - - - - - - - - - - Description - - - - - - - Safety factor applied on the loads - - - - - - - - Rotational rates around centre of gravity - - - - - - - Enumeration flag stating the typ of the load - case (i.e. limit or ultimate loads) - - - - - - - - - - - - - Angle of sideslip [deg] - - - - - - - Angle of attack [deg] - - - - - - - - - - - - - - - - Flight loads - - - Loads resulting from the load case analysis - - - - - - - - - - - - - - - - - - - - - Flight path - - - Definition of a flight path by points of longitude, latitude and a descriptive waypoint code. - - - - - - - - - - Vector of waypoint codes. If waypoint codes are not available put empty items into the waypoint string - - - - - Vector of waypoint latitude values in [deg] - - - - - Vector of waypoint longitude values in [deg] - - - - - Indicates the type of the way point. - - - - - - - - - - - - - - - - - - - - Performance cases - - - List of performance cases - - - - - - - - - - - - - - - - - - - Performance case - - - - - - - - - - - - - - Name - - - - - - - Description - - - - - - - UID of flight performance requirement - - - - - - - - - - - - - - - - - - - - - - - Results of the landing analysis - - - - - - - - - - - - - Determined landing distance. - - - - - - Determined ground phase distance. - - - - - - - - - - - - - - - Level flight - - - - - - - - - - - - - - Specific excess power - - - - - - - - - - - - - Flight performance requirements - - - Contains a list of flight performance requirements - - - - - - - - - - - - - - - - - - - - Flight performance requirement - - - - - - - - - - - - - Name of the performance case - - - - - Description of the performance case - - - - - - Reference to the considered weightAndBalance case - - - - - The UID of the mission to be flown - - - - - List of point performance uIDs constraining the mission - - - - - - - - - - - - - - - - Results of the take-off analysis - - - - - - - - - - - - - Main element containing the results for - take-off calculations optimized for min-imum liftoff speed - VLOFmin. - - - - - Main element containing the results for - take-off calculations optimized for min-imum safety speed V2min. - - - - - - - - - - - - - - Turn - - - - - - - - - - - - - ... - - - - - ... - - - - - - - - - - - - - Flight Cases - - - - - - - - - - - - - - - - - - - - - - - - flightPointType - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Flights - - - Flighs type, containing all flight definitions - - - - - - - - - - - - - - - - - - - - Flight systems - - - - - - - - - - - - - - - - - - - - - - flightType - - - Flight type, containing data of a scheduled flight - - - - - - - - - - MissionUID for the flights mission definition - - - - - ModelUID of the aircraft appointed to perform the flight - - - - - Departure day of the flight - - - - - Time of departure - the time is defined as SOBT (Scheduled Off-Block Time) / STD (Scheduled Time of Departure) - - - - - Arrival day of the flight - - - - - Time of arrival - the time is defined as SIBT (Scheduled In-Block Time) / STA (Scheduled Time of Arrival) - - - - - Reference to the operating airline of a flight - - - - - - - - - - - - - - - floorPanelsType - - - FloorPanels type, containing floor panel definitions - - - - - - - - - - - - - - - - - - - - floorPanelAssemblyPositionType - - - FloorPanelAssemblyPosition type, containing a floor - panel assembly position - - - - - - - - - - x coordinate of the begin of the floor panel - (absolute value) - - - - - x coordinate of the end of the floor panel - (absolute value) - - - - - UID of the first long. floor beam to be - connected to the floor panel - - - - - UID of the second long. floor beam to be - connected to the floor panel - - - - - UID of structural sheet element used for the - floor panel - - - - - - - - - - - - - - - Flying qualities - - - Provides a list of flying qualities cases - - - - - - - - - - - - - - - - - - - - Flying qualities case - - - - - - - - - - - - - Name - - - - - Description - - - - - Aircraft Class; Class 1 small light aircraft; - Class 2 medium weight aircraft, low to medium maneuverability; - Class 3 large, heavy aircraft, low to medium maneuverability; - Class 4 high maneuverability aircraft - - - - - Flight Phase Category; Category A Non-terminal - flight phases requiring maneuvering, precision tracking, or - precise flight-path control (e.g. air-to-air combat, terrain - following). Category B Non-terminal Flight Phases with gradual - maneuvers and without precision tracking, although accurate - flight-path control may be required (e.g. climb, cruise). - Category C Terminal Flight Phases are normally accomplished - using gradual maneuvers and usually require accurate flight-path - control (takeoff, approach and landing). - - - - - main element containing longitudinal transfer - functions - - - - - main element containing lateral directional - transfer functions - - - - - main element containing characteristic - parameters of the handling qualities criteria - - - - - - main element containing handling qualities - ratings - - - - - - - - - - - - - - fqCharParametersType - - - - - - - - - - - - - static margin [-] - - - - - main element containing characteristic - parameter of phugoid damping - - - - - main element containing characteristic - parameters of short period mode criteria - - - - - main element containing characteristic - parameters of roll oscillation criterion - - - - - coupling of roll and spiral mode: normal = no - coupling of roll and spiral mode coupled = coupling of roll and - spiral mode - - - - - main element containing characteristic - parameters of lateral eigenvalues - - - - - main element containing characteristic - parameters of effective roll time constant criterion - - - - - - main element containing characteristic - parameters of roll performance criterion - - - - - - - - - - - - - fqEiglatType - - - - - - - - - - - - - natural frequency of dutch roll mode [rad/s] - - - - - - damping of dutch roll mode [-] - - - - - - roll time constant [s] - - - - - time to double of spiral mode [s] - - - - - - ratio of bank to sideslip angle [-] - - - - - - natural frequency of coupled rollspiral motion - [rad/s] - - - - - damping ratio of coupled roll-spiral motion - - - - - - product of roll-spiral damping and natural - frequency [rad/s] - - - - - handling qualities level of roll time constant - - - - - - handling qualities level of roll spiral mode - - - - - - - - - - - - - - fqLateralType - - - - - - - - - - - - - numerator of transfer function roll control - surface deflection to bank angle - - - - - numerator of transfer function roll control - surface deflection to yaw rate - - - - - numerator of transfer function roll control - surface deflection to sideslip angle - - - - - numerator of transfer function roll control - surface deflection to bank angle of reduced 4th order system - - - - - - numerator of transfer function roll control - surface deflection to sideslip angle of reduced 4th order system - - - - - - numerator of transfer function yaw control - surface deflection to yaw rate - - - - - numerator of transfer function yaw control - surface deflection to sideslip angle - - - - - numerator of transfer function roll stick - input to roll rate - - - - - numerator of transfer function roll stick - input to yaw rate - - - - - numerator of transfer function roll stick - input to bank angle - - - - - numerator of transfer function roll stick - input to sideslip angle - - - - - numerator of transfer function pedal input to - roll rate - - - - - numerator of transfer function pedal input to - yaw rate - - - - - numerator of transfer function pedal input to - bank angle - - - - - numerator of transfer function pedal input to - sideslip angle - - - - - denominator of lateral motion - - - - - - denominator of lateral motion of reduced 4th - order system - - - - - - - - - - - - - fqLongitudinalType - - - - - - - - - - - - - numerator of transfer function pitch stick - input to pitch rate - - - - - numerator of transfer function pitch control - surface deflection to pitch angle - - - - - numerator of transfer function pitch stick - input to pitch angle - - - - - numerator of transfer function pitch stick - input to angle of attack - - - - - numerator of transfer function pitch stick - input to vertical load factor - - - - - denominator of longitudinal motion - - - - - - - - - - - - - - fqPhugoidType - - - - - - - - - - - - - damping ratio of phugoid mode [-] - - - - - - time to double amplitude of unstable phugoid - mode [s] - - - - - - - - - - - - - fqRatingsType - - - - - - - - - - - - - handling qualities level of phugoid damping - - - - - - handling qualities level of C* criterion - - - - - - main element containing handling qualities - levels of short period mode - - - - - main element containing handling qualities - levels of roll oscillation criterion - - - - - main element containing handling qualities - levels of lateral eigenvalues - - - - - handling qualities level of effective roll - time constant - - - - - handling qualities level of roll performance - - - - - - - - - - - - - - fqRollPerfType - - - - - - - - - - - - - time to reach critical bank angle [s] - - - - - - critical bank angle that has to be reached - [deg] - - - - - - - - - - - - - fqRoloscType - - - - - - - - - - - - - ratio of oscillatory component of the roll - rate to the average roll rate [-] - - - - - phase angle of dutch roll oscillation in - sideslip [deg] - - - - - phase angle between roll rate and sideslip in - dutch roll mode [deg] - - - - - ratio of first minimum roll rate to first - maximum [-] - - - - - handling qualities level of ratio of - oscillatory component of roll rate to average roll rate - - - - - - - - - - - - - - fqShortPeriodType - - - - - - - - - - - - - steady state normal acceleration change with - angle of attack [g/rad] - - - - - short period natural frequency of reduced - order system [rad/s] - - - - - short period damping ratio of reduced order - system [-] - - - - - equivalent pitch time delay of reduced order - system [s] - - - - - handling qualities level of CAP criterion - - - - - - - - - - - - - - fqTreffType - - - - - - - - - - - - - effective roll time constant [s] - - - - - - time where tangent of bank angle step response - is placed [s] - - - - - - - - - - - - - framesAssemblyType - - - FramesAssembly type, containing frames assembly - - - - - - - - - - - - - - - - - - - - frameType - - - frame type, containing frame definition (V1.5+) - - - - - - - - - - - - - - - - - - - - - freePathType - - - - - - - - - - - - - - - - - - - - - - - Frustum - - - A cone is defined with a default volume of 1m3. - - - - - - - - - - Upper radius (default=squareRoot(1/pi)=0.56419) [m] - - - - - Upper radius (default=squareRoot(1/pi)=0.56419) [m] - - - - - Height (default=1) [m] - - - - - - - - - - - - - mass - - - - - - - - - - - - - - - - - - - - - - Fuel Mass Fraction - - - Describing the mass fraction considered for a mission segment sequence - - - - - - - - - - Reference to the segment from which the fuel fraction should be considered - - - - - Reference to the segment to which the fuel fraction should be considered - - - - - Float value of the mass fraction defined as - fraction = m_end / m_start - - - - - - - - - - - - - Definition of different volumes of the fuel tank. - - - - - - - - - - - - - - Theoretical volume if material thicknesses - (ribs, spars, skins, stringers) and systems (fuel pumps, - pipes...) are neglected. - - - - - - - Usable fuel volume aircraft operations. - - - - - - Total real fuel tank volume. - - - - - - - - Factor between the usalbe fuel volume and - the real fuel volume. - - - - - Factor between the real fuel volume and the - theoretical optimum fuel volume. - - - - - - - - - - - - - - - fuselageAeroPerformanceType - - - fuselageAeroPerformance type, containing performance - maps with aerodynamic data of a fuselage. - - - - - - - - - - Reference to the uID of the analysed fuselage - - - - - - References used for the calculation of the - force and moment coefficients of the fuselage (in the fuselage - axis system!) - - - - - Calculated aerodynamic performance maps of the - fuselage - - - - - - - - - - - - - fuselageCutOutsType - - - fuselageCutOuts type, containing fuselage cutouts - - - - - - - - - - - - - - - - - - - - fuselageCutOutType - - - fuselageCutOut type, containing a fuselage cutout - definition - - - - - - - - - - Name of the cutout - - - - - Description of the cutout - - - - - X position of the cutout center point - - - - - - Y offset of the cutout reference point - - - - - - Z offset of the cutout reference point - - - - - - Angle in degrees of the vector pointing from - the cutout reference point to the cutout center point, measured - relative to the direction of the fuselage z axis. - - - - - - Coordinates of the unit vector defining the - direction of extrusion - - - - - Coordinates of the unit vector defining the - y-axis of the local cutout coordinate system. Must be normal to - the orientationVector. - - - - - This value is used to define the width of the - cutout - - - - - This value is used to define the height of the - cutout - - - - - This value is used to define the width of the - cutout - - - - - This value is used to define the height of the - cutout - - - - - Fillet radius of the cut element (absolute - value) - - - - - Cutout type. Determines the type of the cutout - and how it is treated by the tools. Possible values: - ("window"|"door"|"ramp") - - - - - - - - - - - - - - - - - - - - - - - - - - fuselageElementsType - - - FuselageElements type, containing the elements of a - fuselage section - - - - - - - - - - - - - - - - - - - fuselageElementType - - - FuselageElement type, containing fuselage element data - - - - - - - - - - - Name of fuselage element - - - - - Description of fuselage element - - - - - - Reference to a fuselage profile - - - - - - - - - - - - - - - - List of fuel tanks - - - - - - - - - - - - - The fuselage fuel tank geometry is defined by a link to a fuselage geometry compartment. -The fuel tank volume type should also be used for the wing fuel tank - - - - - - - - - - - - - - fuselageProfilesType - - - FuselageProfiles type, containing fuselage profile - geometries. See profileGeometryType for further documentation - - - - - - - - - - - - - - - - - - - - fuselagesAeroPerformanceType - - - fuselagesAeroPerformance type, containing - fuselagesAeroPerformance - - - - - - - - - - - - - - - - - - - fuselageSectionsType - - - FuselageSections type, containing fuselage sections - - - - - - - - - - - - - - - - - - - - fuselageSectionType - - - FuselageSection type, containing fusleage section and - element data - - - - - - - - - - Name of fuselage section - - - - - Description of fuselage section - - - - - - - - - - - - - - - - - fuselageSegmentsType - - - FuselageSegments type, containing fuselage segment - definitions (from sections and elements) - - - - - - - - - - - - - - - - - - - fuselageSegmentType - - - FuselageSegment type, containing data of a fuselage - segment - - - - - - - - - - Name of fuselage segment - - - - - Description of fuselage segment - - - - - - Reference to element from which the segment - shall start - - - - - Reference to element at which the segment - shall end - - - - - Optional and additional guidecurves to shape - the outer geometry. - - - - - - - - - - - - - - Structural mounts - - - - - - - - - - - - - - - - - - - fuselageStructureType - - - FuselageStructure type, containing data of the fuselage's - structure - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Fuselages - - - Fuselages type, containing the fuselages of the - configuration - - - - - - - - - - - - - - - - - - - fuselageType - - - - Fuselage type, containing all data related to a - fuselage - - - - - - - - - - - - - - - Name of fuselage - - - - - - - Description of fuselage - - - - - - - UID of part to which the fuselage is - mounted (if any) - - - - - - - - - - - - - - - - - - - - - - - - - Galley elements - - - Galley element collection type - - - - - - - - - - Galley element for use in the decks - - - - - - - - - - - - - Galley element - - - Galley element type, containing the base elements of the cabin - - - - - - - - - - Description - - - - - - - Number of trolleys - - - - - - - - - - - - - - Galleys - - - Galley instance collection type. - - - - - - - - - - Galley - - - - - - - - - - - - - Gas turbines - - - - - - - - - - - - - - - - - - - GasTurbine - - - - - - - - - - - - - - - Gear boxes - - - - - - - - - - - - - - - - - - - Gear box - - - - - - - - - - - - - - - This type contains a list of gears and their deflection - vectors - - - - - 0. General overview - - In this type, a list of gears is defined. - - - - - - 1. - <gear> - (mandatory) - - - One of these nodes per deflected gear is required - here. - - - - - - - - - - - - - - - - - - - - - - This type contains a vector of deflection values for a - single gear - - - - - 0. General overview - - In this type, a vector of deflections of a single - gear is specified. - - - - - 1. - <gearUID> - (mandatory) - - - A reference to a gear from the aircraft model - - - - - - 2. - <controlParameters> - (mandatory) - - - A vector of control parameters of the selected - gear - - - - - - - - - - - - - Reference to a gear - - - - - Control parameters of the gear - - - - - - - - - - - - - - stringerFramePositionType - - - stringerFramePosition type, containing individual - stringer / frame position definition (CPACS V2.1+) - - - - - - - - - - - - - - - - - - - - - Continuity definition for profile extrusion: - 0= C0 (allows sharp edges, default), 2= C2 (defines curvature - continuity) - - - - - - - - - - - - - Definition of interpolation between different - profiles: 0= no interpolation 1= interpolation of structural - profile - - - - - - - - - - - - - - - - - - - - - - generalStructuralMembersAssemblyType - - - generalStructuralMembersAssembly type, containing - structural member assemblies - - - - - - - - - - - - - - - - - - - generalStructuralMemberType - - - - - - - - - - - - - - - - - - - - - - - - Generators - - - - - - - - - - - - - - - - - - - Generator - - - - - - - - - - - - - - - Generic components - - - - - - - - - - - - - - - - - - - genericCostType - - - - - - - - - - - - - - - - - - - - - - - - Generic floor elements - - - Generic floor element collection type - - - - - - - - - - Generic floor element for use in the decks - - - - - - - - - - - - - Generic floor modules - - - Generic floor module instance collection type. - - - - - - - - - - Generic floor module - - - - - - - - - - - - - Global design parameters - - - - - - - - - - - Inner radius of the cylinder - - - - - Inner length of the cylinder - - - - - - - - - - - - - - - Generic fuel tank - - - - - - - - - - - - - - - - - - - - - - Cryogenic tank - - - - - - - - - - Name - - - - - - Description - - - - - - - - - - Burst pressure - - - - - - - - - - - - - - genericGeometricComponentType - - - - In some cases additional geometric components need to - be linked to a CPACS, but these components are not yet handled by - CPACS explicitly. For example, a belly fairing and/or external - tanks. - A generic geometric component may be applied to include - such a geometry from an external file (preferably STEP) in the - context of the overall aircraft. - - - - - - - - - - - - - - Name of genericGeometricComponent - - - - - - Description of genericGeometricComponent - - - - - - UID of part to which the component is mounted - (if any) - - - - - - - - - - - - - - - - - Generic geometric components - - - - - - - - - - - - - - - - - - - - - - Generic geometry component - - - - - - - - - - - - - - - - - - - - - - - Mass description - - - - - - - - parentUID - not set - - - parentUID - set - - - - - location - without - refType - - global - local - - - - location - with - refType="absLocal" - - global - local - - - - location - with - refType="absGlobal" - - global - global - - - - Note: - The combination of - location - with - refType="absLocal" - and no - parentUID - is global, because the local coordinate system to which the - location - is referring to via - refType - equals the global coordinate system. - - - - - ... - - - ... - - - ... - - - ... - - - ]]> - - - - - ... - - - ... - - - ... - - - ... - - - ]]> - - - - - ... - - - ... - - - ... - - - ... - - - ]]> - - - - wingUID - - ... - - - ... - - - ... - - - ... - - - ]]> - - - - wingUID - - ... - - - ... - - - ... - - - ... - - - ]]> - - - - wingUID - - ... - - - ... - - - ... - - - ... - - - ]]> - - - - - - - - - - - - Name - - - - - Description - - - - - UID of the component which serves as parent element, i.e. whose coordinate system is to be used as a reference for the mass properties (CoG location, orientation and massInertia). Thus, two cases can occur: (1) - it is set: local coordinate system of the parent; (2) it is not set: global CPACS coordinate system. - - - - - - UID of the geometric description of the component. - - - - - - Mass [kg] - - - - - Mass location. - If the optional refType attribute is set, it explicitly specifies whether the location of the mass refers to the global CPACS coordinate system (absGobal) or the local coordinate system of the parent element (absLocal, given by the CPACS hierarchy OR by parentUID). - If it is not set, the global CPACS coordinate system is considered as default. - To ensure consistency, the same settings apply as well to orientation and massInertia. - - - - - - Orientation. The reference coordinate system (absGlobal or absLocal) is identical to location. - - - - - Mass inertia. The reference coordinate system (absGlobal or absLocal) is identical to location. - - - - - - - - - - - - - - genericSystemsType - - - Node for geometrical layout of system components - based on simple geometric shapes - - - - - - - - - - - - - - - - - - - Generic system - - - - - - - - - - Name - - - - - Description - - - - - - - - - - - - - - - geographicPointConstraintType - - - Geographic point constraint, containing a longitude, latitude, altitude data triplet. - - - - - - - - - - - Longitude coordinate 0-360 - - - - - - - - - - - - Latitude coordinate 0-360 - - - - - - - - - - - - Altitude in meters - - - - - - - - - - - - - - - - - - - geographicPointType - - - Geographic point type, containing a longitude, latitude, altitude data triplet. - - - - - - - - - - Longitude coordinate 0-360 - - - - - Latitude coordinate 0-360 - - - - - Altitude in meters - - - - - - - - - - - - - - Geometry - - - - - - - - - - - - - - - - - - - - - - airfoilAeroPerformanceType - - - airfoilAeroPerformance type, containing performance maps - with aerodynamic data of an airfoil. - - - - - - - - - - References used for the calculation of the - force and moment coefficients - - - - - Calculated aerodynamic performance maps of the - full configuration - - - - - - - - - - - - - globalBeamPropertiesType - - - globalBeamPropertiesType, containing the global beam - properties such as EA, EI, mass - - - - - - - - - - - - - - - - - - - - - - - - - - - Flight point - - - - - - - - - - - - - - - - - - - - Mach number - - - - - - - Calibrated air speed - - - - - - - True air speed - - - - - - - - - - - - - - - - - Performance Cases - - - - Specification of performance cases required for the performance evaluation of air vehicles (aircraft, rotorcraft, etc.). - - The information in this node is - generally - applicable to any kind of vehicle. - Vehicle-specific - information is provided through the performanceRequirements node found under: - /cpacs/vehicles/../model/performanceCases - . - - - - - - - - - - - - - - - - - - - - - - Ground load Cases - - - - - - - - - - - - - - - - - - - - - - guideCurveProfileGeometryType - - - - A guide curve profile is defined by a profile name, an - optional description and a 3-dimensional relative pointlist with - all three coordinates mandatory. For typical profiles, one of - the coordinate vectors contains only "0" entries. All point - coordinates are transferred to the global coordinate system. - First and last point may, but need not to, be identical. - - The points have to be ordered in a mathematical - positive sense. - A profile can be symmetric. In that case the profile - is interpreted as being not closed and will be closed by - mirroring it on the symmetry plane. - Curves have to go continuously over the whole wing or - fuselage - Connection of guide curves from segment to segment - - - - - - - - Please note, currently it is not possible to apply any - means of class based transformation in the description. However, - this may be an addition for the future. - - - - - - - - - - - Name of profile - - - - - Description of profile - - - - - - - - - - - - - - - - guideCurveProfilesType - - - Guide Curve Profiles type. This type is used to - describe guide curves that enable designers to create a geometry - that deviates from a standard loft. - - - - - - - - - - - - - - - - - - - - Guide Curves Type - - - Guide Curve type. This type is used to describe guide - curves that enable designers to create a geometry that deviates - from a standard loft. - - - - - - - - - - - - - - - - - - - Guide Curve Type - - - - A guide curve may be used to alter the shape of the - outer geometry and "guide" the loft. - The guide curve profiles are defined in the guideCurveProfileGeometryType. - Their use on wing and fuselage components is illustrated in the image below. - - - - - - - - - - - - - - - Name of guide curve - - - - - Description of guide curve - - - - - Reference to a guide curve profile - - - - - - For the first segment fromGuideCurveUID is not - a valid entry! For the first guideCurve - fromRelativeCircumference must be applied! fromGuideCurveUID is - exclusive. - - - - - - Reference to the previous guide curve from - which this guide curve shall start. - - - - - - Continuity definition for geometry - generation. Possible options: C0, C1 from previous, C2 from - previous, C1 to previous, C2 to previous - - - - - - - - - - - - - - - - - - - Reference to the relative circumference - position from which the guide curve shall start. Valid values - are in the interval -1.0...1.0. - - - - - - Tangent at first point - - - - - - - - The relative circumference - position at which the guide curve shall end. Valid values - are in the interval -1,..,1. - - - - - - Tangent at last point - - - - - - Local direction along which the relative x-coordinates of - the guide curve points are defined. For the wing the default is - the wing's local x-axis, for the fuselage its the fuselage's local z-axis. - - - - - - - - - - - - - - - CPACS header - - - Header type, containing CPACS dataset description - - - - - - - - - - - Name of CPACS dataset - - - - - Description of CPACS dataset - - - - - - Version of initial CPACS dataset according to the Semantic Versioning 2.0.0 standard. - - - - - - DEPRECATED: Should only be set to allow TiGL to open the file until TiGL is adopted accordingly. - Will be replaced by the cpacsVersion element in versionInfos. - - - - - - - - - - - - - - - Heat exchangers - - - - - - - - - - - - - - - - - - - Heat exchanger - - - - - - - - - - - - - - - Heat flow - - - - - - - - - - - Heat flow value - - - - - - - - - - - - - - - - - - Heat flow - - - - - - - - - - - Heat flow value - - - - - - - - - - - - - - - - - - hingeMomentsMapType - - - hingeMomentsMap type, containing a hinge moments map - with aerodynamic data. Array order is: angleOfAttack min->max - then angleOfSideslip then reynoldsNumber then machNumber. - All coefficients in the aeroperformanceMap relate to - the CPACS coordinate system. See documentation of the - CPACS-Element for further information. - - - - - - - - - - Name of the AeroPerformanceMap. - - - - - - Description of the AeroPerformanceMap. - - - - - - Mach number - - - - - Reynolds Number - - - - - Sideslip angle - - - - - Angle of attack - - - - - - - - - - - - - - htpFwdInterfaceDefType - - - Definition of the interface of forward HTP attachment - - - - - - - - - - Definition of the forward HTP attachment - interface - - - - relative width of reinforcement at fwd HTP - attachment, between 0.0 and 1.0 - - - - - relative width of plate at fwd HTP attachment - (only applicable for Type1 model), between 0.0 and 1.0, smaller - than htpPlateWidth - - - - - UID of panel element at HTP forward attachment - in x-direction (shell elements) - - - - - UID of panel element at HTP forward attachment - in z-direction (shell elements) - - - - - UID of reinforcements for panel element at HTP - forward attachment in z-direction (beam elements) - - - - - - UID of the element to fix HTP to fuselage - (beam elements) - - - - - - - - - - - - - - htpInterfaceDefType - - - Definition of the interface of HTP - - - - - - - - - Definition of the HTP interface - - - - - UID of the fuselage frame at the forward HTP - attachment - - - - - - UID of the fuselage frame at the backward HTP - attachment - - - - - - maximum HTP deflection (nose up in - degrees) - - - - - - maximum HTP deflection (nose down in - degrees) - - - - - - angle of the reinforcements at backward HTP - attachment - (in degrees) - - - - - - Defines area (absolute) in x-direction around - htpFrame2UID where the HTP attachmentpoint has correct position - ==> check and potentially warning message - - - - - Defines area (absolute) in y-direction around - the - outer edge of htpFrame2UID where the HTP attachmentpoint has correct - y-position ==> check and potentially warning - message - - - - - - Defines allowed z-position for rear HTP - attachment - relative to total frame height ==> check and potentially warning - message ==> check and potentially warning - message - - - - - - Definition of HTP structural - elements - - - - - - Definition of HTP forward attachment to - structure - - - - - - - - - - - - - - - htpStructElemDefType - - - definition of structural elements in HTP attachment - - - - - - - - - - Definition of tailplane attachment area - (Standard Configuration) - - - - UID of structural element for HTP front - crossbeams - - - - - UID of structural element for HTP rear - crossbeams - - - - - UID of structural element for HTP diagonal - beams - - - - - UID of structural element for HTP side beams - - - - - - UID of structural element for upper HTP cutout - reinforcement beams, also used for lower cutout reinforcement, - when not explicitly defined - - - - - UID of structural element for lower HTP cutout - reinforcement beams (optional) - - - - - - - - - - - - - - Skin Layers - - - - - - - - - - - - - - - - - - - - - - - Structure - - - - - - - - - - - - - - - - - - - - - - - - Hulls - - - - - - - - - - - - - - - - - - - Hulls - - - - - - - - - - Name - - - - - - Description - - - - - - - - - - - - - - - - - - - - indirectOperatingCostType - - - - - - - - - - - - - - - - - - - - - - Individual system categories - - - - - - - - Generic - - - - - - - - - - - integerBaseType - - - Base type for integer nodes (including external data - attributes) - - - - - - - - - - - - - - - - - - - List of fuselage fuel tanks integrated in compartments. - - - - - - - - - - - - - The integral fuel tank geometry is defined by a link to a fuselage geometry compartment. -The fuel tank volume type should also be used for the wing fuel tank - - - - - - - - - - - - - interConnectionStrutAttachmentType - - - - - - - - - - - - - Definition of the position of the attachment - joint in relative coordinates. - - - - - Material settings of the attachment. - - - - - - - - - - - - - - interconnectionStrutsType - - - - - - - - - - - - - Definition of one interconnection strut. - - - - - - - - - - - - - - interconnectionStrutType - - - - - - - - - - - - - uID of control surface where this flap is - attached to by the interconnection strut. - - - - - Material settings of the strut (if strut is - modeled as a simple strut). - - - - - Definition of the attachment on this control - surface. - - - - - Definition of the attachment on the other - control surface - - - - - Free path in positive (tensil) and negative - (compression) direction before interconnection strut blocks. - - - - - - - - - - - - - - - intercostalPositionType - - - intercostalPosition type, containing the position of intercostals - in DSS - - - - - - - - - - - - UID of the frame at which intercostal - starts - - - - - UID of the forward door frame - - - - - UID of the door - - - - - non-dimensional value ranging between 0 and 1 - - - - - - UID of profileBasedStructuralElement used for - intercostal - - - - - - - - - - - - - - IntercostalsAssemblyType - - - IntercostalsAssembly type, containing intercostal - definitions - - - - - - - - - - - - - - - - - - - structuralElementsConnectionsType - - - StructuralElementsConnections type, containing - connections between structural elements - - - - - - - - - - Flag for automatic generation of interface - definitions (draft version) - - - - - - - - - - - - - - - Isotensoid dome - - - - - - - - - - Radius of the fitting/smaller polar opening - - - - - - - - - - - - - Isotropic material properties - - - - Defines the material properties for an isotropic material. Note that the shear modulus G - is defined in terms of the elastic modulus E and the Poisson's ratio nu as: - - - - Specifying a value for all three properties E, G and nu therefore results in an overdetermined material definition and must be avoided. - - - - - - - - - - - - Young's modulus [N/m^2] - - - - - - - Shear modulus [N/m^2] - - - - - - - Poisson's ratio - - - - - - - Thermal expansion coefficient [1/K] - - - - - - - Thermal conductivity of the material in - [W/(m*K)] - - - - - - - Allowable stress for tension [N/m^2] - - - - - - - Allowable stress for compression [N/m^2] - - - - - - - Allowable stress for shear [N/m^2] - - - - - - - Allowable strain for tension - - - - - - - Allowable strain for compression - - - - - - - Allowable strain for shear - - - - - - - Yield strength, tension [N/m^2] - - - - - - - Yield strength, compression [N/m^2] - - - - - - - Plastification curves for isotropic - materials incl. element elimination - - - - - - - Optional knockdown factor for fatiuqe - (defaults to 1) - - - - - - - Fatigue behaviour of the material - - - - - - - Damage tolerance behaviour of the - material - - - - - - - - - - - - - - Landing gear base - - - - Base type for landing gears (i.e. nose gear, main gear and skid gear). - An example of a nose and main gear is shown below: - - - - - - - - - - - - - - Name - - - - - Description - - - - - UID of the parent component. If set, the position of the main strut is defined relative to the parent coordinate system. - - - - - - - - - Total length of landing gear, equals the distance from the middle of the bogie/axles to the axis of rotation of the pintle strut. Distance is measured while landing gear is fully extended and in airborne condition (i.e., if a spring is present, the totalLength includes the springDeflectionLength) - - - - - Static suspension travel means the positive distance between the total length in airborne condition and the reduced length due to compression on the ground. - - - - - Compressed suspension travel means the positive distance between the total length in airborne condition and the maximum reduced length due to maximum compression on the ground (e.g., landing shock). - - - - - - - Transformation with respect to the uppermost point of the main strut. From this point the landing gear is oriented in negative z-direction by default. - - - - - - - - - - - - - - - Braking function - - - - - Describes the braking state of the landing gear. - - - - - - - - - - Control parameter indicating that the brake is set - - - - - Control parameter indicating that the brake is released - - - - - - - - - - - - Assembly of landing gear components - - - - - Describes an assembly of the various landing gear components - - - - - - - - - - - - Main strut - - - - - - - - - - Drag strut (Assumption: one end of the strut will connect to the main strut and the other end will be given as endPoint) - - - - - - - - - - - - - - Landing gear control functions - - - - - A list of functions which can be addressed by the controlDistributor. - - - - - - - - - - Extension path - - - - - Steering path - - - - - Braking state - - - - - - - - - - - Landing gear control parameters - - - - Parameters of a landing gear control such as extraction or steering. - - - - - - - - - - - - Retraction angle of the main landing - gear. Equals a rotation around the - global z-axis in degrees. 0 = retraction - to the front; 90 = retraction to the - left; 180 = retraction to the rear; 270 - = retraction to the right. - - - - - - - - Distance of the center of rotation to the top of the main strut - for retracting and extending the landing gear. I.e., a value of - 0 means that the landing gear will rotate around the upper end - of the main strut during retraction. If this value is greater - than 0, the center of rotation is shifted by this value above - the main strut end point (translation along the main strut axis). - - - - - - - - - - - - - - Extension step - - - - - Describes a step with the extension path of the landing gear. Make sure to provide a least one step with stepType=extracted! - - - - - - - - - - Step type (retracted or extracted) - - - - - - - - - - - - Control parameter - - - - - Extension angle of the main strut [deg] - - - - - - - - - - - Extension path - - - - - Describes the extension path of the landing gears via a list of steps. - - - - - - - - - - Step within the extension path - - - - - - - - - - - - landingGearInterfaceDefinitionsType - - - CenterFuselage landing gear interface definitions - - - - - - - - - - - - - - - - - - - - - - - - - - keelbeamType - - - HighWingCenterFuselage / Keelbeam definition between - mainframe1 und mainframe2 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - lateralPanelsType - - - HighWingCenterFuselage / lateral Panel definition - between mainframe1 und mainframe2 - - - - - - - - - - - - - - - - - - - - - - - - - - longFloorBeamConnectionType - - - HighWingCenterFuselage / Long. floor beam connection - - - - - - - - - - - - - - - - - - - - - centerFuselageMainFramesType - - - High wing main frame definition, containing mainframe - UIDs - - - - - - - - - - - - - - - - - - - - - - - pressureFloorType - - - High Wing Center Fuselage / pressure floor definition - between mainframe1 und mainframe2 - - - - - - - - - - - - - - - - - - - - - - - sideboxType - - - HighWingCenterFuselage / side box definition between - mainframe1 und mainframe2 - - - - - - - - - - - - - - - - - - - - - - Landing gear position safety margins - - - LandingGearPositionSafetyMargins type, containing the - safety margins of the gear due to its position - - - - - - - - - - Safety margin for landing gear x position - regarding tail clearance at takeoff pitch angle - - - - - - Safety margin for landing gear x position to - avoid tail dropping down during touchDown and ground maneuvering - - - - - - Safety margin for landing gear y position to - avoid wing tip dropping down during ground maneuvering - - - - - - Safety margin for landing gear y position - regarding wingtip or engine nacelle clearance at a certein roll - angle - - - - - - - - - - - - - Steering step - - - - - Describes a step with the steering path of the landing gear. - - - - - - - - - - Step type (centered, fullBackboard or fullStarboard) - - - - - - - - - - - - Control parameter - - - - - Steering angle [deg] - - - - - - - - - - - Steering path - - - - - Describes the steering path of the landing gears via a list of steps. - - - - - - - - - - Step within the steering path - - - - - - - - - - - - - Definition of the wing attachment - - - - - Definition of the wing attachment, if - attached to the wing. The definition - includes the position of the landing gear as - well as the information to which spars resp. - supportBeam the gear is attached. - - - - - - - - - - - - UID of the second spar, where the landing gear is attached to. Only used, if the landing gear is attached between two spars. - - - - - - UID of a set of ribs (ribDefinition) - - - - - Number of the rib in the rib set (ribDefinition) - - - - - - - - UID of the structural mount - - - - - - - - - - - - - - - Landing gears - - - Contains a list of landing gears. - - - - - - - - - - - - - - - - - - - Definition of the main landing gear support beam - position - - - Definition of the main landing gear support beam - position - - - - - - - - - - Relative chordwise coordinate (xsi) of the - inner end of the support beam. The eta - position of the inner end is defined by the eta position of the - wing root (=wing-fuselage attachment). - - - - - Relative spanwise coordinate (eta) of the - outer end of the support beam. The xsi - coordinate of the outer end is defined by the spar position - (first spar), where the support beam is attached to. - - - - - - - - - - - - - - Landing gears - - - LandingGear type, containing the definition of nose, - main and skid gears. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Lavatories - - - Lavatory instance collection type. - - - - - - - - - - Lavatory - - - - - - - - - - - - - Lavatory elements - - - Lavatory element collection type - - - - - - - - - - Lavatory element for use in the decks - - - - - - - - - - - - - Definition of the wings leading edge devices. - - - - Definition of the wings leading edge devices. - - - - - - - - - - - - - - - - - - - - Trailing edge device of the wing. - - - A leadingEdgeDevice (LED) is defined via its outerShape - relative to the componentSegment. The WingCutOut defines the area - of the skin that is removed by the LED. Structure is similar to - the wing structure. The mechanical links between the LED and the - parent are defined in tracks. The deflection path is described - in path. Additional actuators, that are not included into a - track, can be defined in actuators. - Leading and trailing edge are defined by the outer - shape of the wing segments, i.e. the trailing edge of a - trailingEdgeDevice is the trailing edge of the wing. This is also - valid for kinks that are present in the wing but not explicitly - modeled in the control surface. - The edges of the control surface within the wing are a - straight line in absolute coordinates! Hence, there needs to be a - straight connection between the eta-wise outer and inner points - of the edge that is within the wing in absolute coordinates. - - - - - - - - - - - Name of the leading edge device. - - - - - - Description of the leading edge device. - - - - - - UID of the parent of the LED. The parent is - the componentSegment, where it is attached to. - - - - - - - - - - - - - - - - - - - - - Optional definition of the airfoil inner shape of - leading edge devices (LED). - - - - All parameters are optional. For the definition of the - parameters, please refer to the picture below. Parameters from - the outer border default to the parameters of the inner border. - - - - - - - - - - - - - - - Relative height of the most forward point of - the LED's rear part, based on the airfoil height of the parent - at this position. Optional. - - - - - Relative chordwise position of the most - forward point of the LED's rear part, based on the chord of the - parent at this position. Optional. - - - - - - - - - - - - - Optional definition of the leading edge shape of - trailing edge devices (TED). - - - - All parameters are optional. For the definition of the - parameters, please refer to the picture below. Parameters from - the outer border default to the parameters of the inner border. - - - - - - - - - - - - - - - Relative height of the leading edge of the TED, - based on the airfoil height of the parent at this position. - Optional. - - - - - Relative chordwise upper skin position, of the - border, where the airfoil of the TED is equivalent of the - airfoil from the parent. Measured from the rear to the front (0 - = TED trailing edge; 1 = TED leading edge). Values form the - outer border default to the value of the inner border. Optional. - - - - - - Relative chordwise lower skin position, of the - border, where the airfoil of the TED is equivalent of the - airfoil from the parent. Measured from the rear to the front (0 - = TED trailing edge; 1 = TED leading edge). Values form the - outer border default to the value of the inner border. Optional. - - - - - - - - - - - - - - linerType - - - Liner type, containing liner data - - - - - - - - - - Type of liner - - - - - - - - - - - - - % of fan diameter - - - - - % of fan diameter - - - - - - - - - - - - - Link to file (Step, Iges or Stl) - - - Please provide a link to the additional file that shall - be loaded by the TIGL library. Furthermore it is necessary to - provide the format attribute so that the file type can be - identified. Several CAD formats provide multiple endings, and - hence, this measure seems necessary. - - - - - - - - - - - - - - - - - - - - - - - - - Definition of one fuel tank integrated in a fuselage compartment. - - - The definition of fuselage tanks is still preliminary. - Currently, there is no link to any structural elements - - - - - - - - - - - Name of the fuselage fuel tank. - - - - - - Description of the fuselage fuel tank. - - - - - - Link to the tank geometry defined by a compartment. - - - - - - - - - - - - - - - - - - - Load analysis - - - - - - - - - - - - - - - - - - - - - - - Load application points - - - - Multiple sets of scattered load application points can be defined. However, no specific information about the corresponding loads (e.g. whether aerodynamic or structural loads are involved) or mesh topologies are specified here, as such assumptions are tool-specific. - - - - - - - - - - - - - - - - - - - - Load application point set - - - - - A point set contains discrete spatial points at which loads are applied (e.g., aerodynamic or structural loads). A typical procedure in CPACS is as follows: - - - - - Reference a wing, fuselage or control surface by its - uID - using the - componentUID - node. - - - Define a reference axis through the above component with the - loadReferenceLine - element to specify where a load distribution shall be applied. - - - Compute the intersections with (e.g.) ribs of the referenced component (wing, fuselage or control surface) and write the results into - loadApplicationPoints - . This procedure results from common practice where the forces in structural analyses are typically introduced at structural elements such as ribs and spars. With respect to preliminary aircraft design a two-dimensional load distribution is preferred. However, an arbitrary distribution of the load application points is possible (without the intersection of structural elements with a reference axis in the previous step), for example to define discrete load distributions on the wing surface in streamwise and spanwise direction. - - - Specify the location and orientation of cut loads in the - cutLoadIntegrationPoints - element and the corresponding connectivity information in the - connectivities - node. - - - - - - - - - - - - - - - - - - UID of a wing, fuselage or control surface - - - - - - - Reference axis (line) for load distribution - - - - - - - List of points at which load vectors are - applied to - - - - - - - List of points at which cut loads are applied to - - - - - - - Specification of connectivity properties between points - - - - - - - - - - - - - - - dynamicAircraftModelCoordinatesType - - - - - - - - - - - - - - - - - - - - - - - - - loadBreakdownType - - - - - - - - - - - - - - - - - - - - - - - - - - Accelerations - - - Translational or rotational accelerations acting - on the aircraft - - - - - - - - - - - Rotational accelerations acting around aircraft centre of gravity [deg/s^2] - - - - - - - - - - - - - Gust definition - - - The coordinate system of the gust corresponds to the CPACS coordinate system. - - - - - - - - - - Parameters describing the shape of the gust - - - - - - - - - - - - - - - - - Angle between gust and vehicle [deg] (e.g., 0deg: from right to left; 90 deg: downwards; 180deg: from left to right; 270/-90deg: upwards) - - - - - - - Gust length: length of ramp or gradient distance of 1-cos gust - - - - - - - Gust velocity - - - - - - - - - - - - - - Load factors - - - - - - - - - - - - - - Load factor in x-direction - - - - - - - Load factor in y-direction - - - - - - - Load factor in z-direction - - - - - - - - - - - - - - Load case specification - - - Input values defining a load case - - - - - - - - - - - Environment - - - - - - - Altitude above sea level - - - - - - - Mach number - - - - - - - UID of the aerodynamic loads (aeroCase) - - - - - - - - Controller description. Note: Since there is no controller description in CPACS yet, the expected content of this string element has to be defined individually for each project. - - - - - - - - - - - UID referencing the mass state of aircraft for this load case - - - - - - - - - - - - - - Load cases - - - - - - - - - - - - - - - - - - - - - - - - - Load case superposition - - - List of uIDs referencing load cases that are superimposed to the current load case - - - - - - - - - - - - UID reference to another load case to be superimposed - - - - - - - - - - - - - - Load case - - - This node defines the load case - - - - - - - - - - - Name of the load case - - - - - - - Description of the load case - - - - - - - - - - - - - - - - - Load envelopes - - - The loads envelope is the results of the loadsAnalysis - and lists those loadcases that are limiting for the design - - - - - - - - - - - - - - - - - - - - Load envelope - - - List of load cases defining a load envelope - - - - - - - - - - - Name - - - - - Description - - - - - UID of the corresponding point set - - - - - - List of uIDs defining the loads envelope - - - - - - - - - - - - - loadReferenceAxisPointsType - - - - - - - - - - - - - - - - - - - - - - loadReferenceAxisPointType - - - - - - - - - - - - - - - - - - - Relative spanwise position. Eta refers to the segment or componentSegment depending on the referenced uID. - - - - - Relative chordwise position. Xsi refers to the segment or componentSegment depending on the referenced uID. - - - - - Relative height position. - relHeight is relative to the local airfoil thickness. - - - - - This reference uID determines the reference coordinate system. - If it points to a segment, then the eta-xsi values are considered to be in segment - eta-xsi coordinates; if it points to a componentSegment, - then componentSegment eta-xsi coordinates are used. - - - - - - - - - - - - - - Load sets - - - - A list of load sets - - - - - - - - - - - - - - - - - - - - Load set - - - A set of forces and moments - - - - - - - - - - - Description - - - - - - - UID of load application point set (analysis/global/loadApplicationPoints) - - - - - - - Force in x-direction [N] - - - - - - - Force in y-direction [N] - - - - - - - Force in z-direction [N] - - - - - - - Moment around x-axis [Nm] - - - - - - - Moment around y-axis [Nm] - - - - - - - Moment around z-axis [Nm] - - - - - - - Nodal displacement in x-direction [m] - - - - - - - Nodal displacement in y-direction [m] - - - - - - - Nodal displacement in z-direction [m] - - - - - - - Nodal rotation around x-axis [deg] - - - - - - - Nodal rotation around y-axis [deg] - - - - - - - Nodal rotation around z-axis [deg] - - - - - - - Load brake-down - - - - - - - - - - - - - - - Log entry - - - - - - - - - - Description of CPACS dataset - - - - - - Timestamp - - - - - - Creator (tool, person, etc.) - - - - - - - - - - - - - - logFloorBeamPositionType - - - longFloorBeamPosition type, containing individual - position definition - - - - - - - - - - UID of structural element - - - - - UID of crossbeam to which the long. beam is - attached - - - - - y position of long. beam - - - - - - Continuity definition for profile extrusion: - 0= C0 (allows sharp edges, default), 2= C2 (defines curvature - continuity) - - - - - - - - - - - - - Definition of interpolation between different - profiles: 0= no interpolation 1= interpolation of structural - profile - - - - - - - - - - - - - - - - - - - - - - longFloorBeamsAssemblyType - - - longFloorBeamsAssembly type, containing long. floor - beam assemblies - - - - - - - - - - - - - - - - - - - longFloorBeamType - - - longFloorBeam type, containing a long. floor beam - definition - - - - - - - - - - - - - - - - - - - - Luggage compartment elements - - - Luggage compartment element collection type - - - - - - - - - - Luggage compartment element for use in the decks - - - - - - - - - - - - - Luggage compartments - - - - - - - - - - Luggage compartment - - - - - - - - - - - - - - Additional Center Tanks - - - - - - - - - - - - - - Additional center tank - - - - - - - - - - - - - Main actuator - - - - Definition of the landing gear main actuator. - - - - - - - - - - - Reference to the main actuator uID of the - landing gear - - - - - - - - - - - - - - Main landing gear - - - List of main gears - - - - - - - - - - - - - - - - - - - mainStrutInterfaceDefinitionsType - - - HighWingCenterFuselage main strut interface definitions - - - - - - - - - - - - - - - - - - - - - - mainStrutFuselageAttachmentType - - - HighWingCenterFuselage / main strut attachment to - fuselage frame and stringer - - - - - - - - - - - - - reference to the structural element that comprises this connection. - - - - - - - - - - - - - - maintenanceCostType - - - - - - - - - - - - - - - - - - - - - - - - mAirConditioningType - - - - - - - - - - - - - Air conditioning mass description - - - - - - - - - - - - - - Mass breakdown - - - - - 1. General - - - The - massBreakeDown - is subdivided in - designMasses - , - fuel - , - payload - and - mOME - (operating empty mass). - - - designMass - - The design masses contain the overall values for - mTOM and so forth. These should be listed as specified by the - TLAR or found from initial sizing. - - fuel - and - payload - - The fuel and payload nodes should contain maximum - values, i.e. full fuel tanks, all passengers on board and full - cargo holding. These values may exceed the maximum allowable - take-off mass as the actual loading of the aircraft should be - specified in the weight and balance section of the aircraft. - - - mOEM - - - The operation empty mass structure is based on the Airbus Mass - Standard brake down [AIRBUS MASS STANDARD 2008]. The - operator’s mass empty (OME) is defined by the sum of the - following component masses: - - operator’s items - manufacturer’s mass empty (MME) - - - - - - - 2. massDescription - - - Each sub component has the following - massDescription - which include a: - - Name - Description - parentUID - Mass value - Mass location - Mass orientation - Mass Inertia. - - - - The - massdescription - can be found at the - designMasses - direct under each item. At the - fuel - , - payload - and - mOME - under massDescription in each item and sub item. - - Concerning symmetry please note that any item - referenced by its UID, e.g. wingUID, accounts for the complete - component, e.g. right and left side. Hence for these items - their complete mass needs to be specified. If the mass of - geometricallly symmetrical components is different, please use - the symmetry modifyers for UIDs: _symm and _mirror. See also - the overall CPACS definition section on symmetry - - - - - - - - - - - - - - - - - - - - - - - - - Mass composition - - - - - - - - - - - - - - - - - - - Mass flow - - - - - - - - - - - Mass flow value - - - - - - - - - - - - - - - - - - Mass flow - - - - - - - - - - - Mass flow value - - - - - - - - - - - - - - - - - - Mass inertia - - - massInertiaType - - - - - - - - - - - - - - - - - - - - - - - - massInertiaVectorType - - - - - - - - - - - - - - - - - - - - - - - - - - - materialDefinitionForProfileBasedPointType - - - MaterialDefinitionForProfileBased type, containing a - material definition (Reference to material and thickness) for - profile based objects, addition point reinforcements - - - - - - - - - - uID of the profile point to which the - additional stiffness shall be applied. - - - - - uID of a material definition. - - - - - - cross sectional area of additional long. - stiffener at strctural element point - - - - - optional auxiliary parameter for special use - (no physical meaning) - - - - - optional auxiliary parameter for special use - (no physical meaning) - - - - - - - - - - - - - Definition of the properties of the structural - profile sheet - - - MaterialDefinitionForProfileBased type, containing a - material definition (Reference to material and thickness) for - profile based objects. - - - - - - - - - - - UID of the sheet to which the material - properties shall be applied - - - - - - Predefined ID of the sheet of a standard profile - - - - - - - - - - - - - - - - - - Length of the sheet of a standard profile [m] - - - - - - - - - uID of a composite definition. - - - - - - Orthoropy direction of the composite. - - - - - - Scaling factor of the composite thickness. - - - - - - - - uID of a material definition. - - - - - - Absolute thickness of the material [m] - - - - - - - - - - - - - - - - Material Definition - - - MaterialDefinition type, containing a material - definition (Reference to material and thickness) - - - - - - - - - choice between composite / isotropic material - definition - - - - - uID of a composite definition. - - - - - - Orthotropy direction of the composite. - - - - - - Scaling factor of the composite thickness. - Absolute thicknesses are defined in each composite material - separately - - - - - - - uID of a material definition. - - - - - - Absolute thickness of the material. - - - - - - - - - - - - - - - Materials - - - Materials type, containing material and composite data. - A material describes the properties of a certain material. - Several materials can be combined within one composite. - - - - - - - - - - - - - - - - - - - - - Material - - - - Definition of the material properties for one of the following - material types: - - isotropic materials - anisotropic 2D and 3D materials - orthotropic 2D and 3D materials - - The nonemclature is adopted from [1] to define the material properties in an orthotogonal 1-2-3 - coordinate system. This may be illustrated by the stresses of a three-dimensional cube: - - - - - [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. - - - - - - - - - - - - Name of the material - - - - - Description of the material - - - - - Material density [kg/m3] - - - - - - - - - - - - Reference temperature for thermal expansion - coefficient [K] - - - - - - - - - - - - - - - - - mAutomaticFlightSystemType - - - - - - - - - - - - - Automatic flight system mass description - - - - - - - - - - - - - - mAuxillaryPowerUnitType - - - - - - - - - - - - - Auxiliary power unit masse description - - - - - - - - - - - - - - Axle - - - - - - - - - - - - - - Axle mass description - - - - - - - - - - - - - - - - mBellyFairingsType - - - - - - - - - - - - - - - - - - - - - - - mBleedAirSystemType - - - - - - - - - - - - - Bleed air system mass description - - - - - - - - - - - - - - Bogie - - - - - - - - - - - - - - Bogie mass description - - - - - - - - - - - - - - - - mBulkCargosType - - - - - - - - - - - - - - - - - - - - - - - mBulkCargoType - - - - - - - - - - - - - - - - - - - - - - mBulkheadsType - - - - - - - - - - - - - - - - - - - - - - - mCabinFloorsType - - - - - - - - - - - - - - - - - - - - - - - mCabinLightingsType - - - - - - - - - - - - - - - - - - - - - - - mCargoFloorsType - - - - - - - - - - - - - - - - - - - - - - - mCargoLiningsType - - - - - - - - - - - - - - - - - - - - - - - mCargoLoadingsType - - - - - - - - - - - - - - - - - - - - - - - Cargo masses - - - - - - - - - - - - - Cargo masses description - - - - - Cargo mass description - - - - - - - - - - - - - - - mCarriagesType - - - - - - - - - - - - - - - - - - - - - - - mCarryOnsType - - - - - - - - - - - - - - - - - - - - - - - mCarryOnType - - - - - - - - - - - - - - - - - - - - - - mCateringsType - - - - - - - - - - - - - - - - - - - - - - - mCellsType - - - - - - - - - - - - - - - - - - - - - - - mCockpitLightingsType - - - - - - - - - - - - - - - - - - - - - - - mCommunicationType - - - - - - - - - - - - - Communication mass description - - - - - - - - - - - - - - mComponentSegmentsType - - - - - - - - - - - - - - - - - - - - - - - mComponentSegmentType - - - - - - - - - - - - - - - - - - - - - - - - - - - - - mControlSurfaceSupportsType - - - - - - - - - - - - - - - - - - - - - - - mControlSurfaceSupportType - - - - - - - - - - - - - - - - - - - - - - - - - mCrewMembersType - - - - - - - - - - - - - - - - - - - - - - - mCrewSeatsType - - - - - - - - - - - - - - - - - - - - - - - mDeIcingType - - - - - - - - - - - - - De-icing mass description - - - - - - - - - - - - - mDocumentsToolsType - - - - - - - - - - - - - - - - - - - - - - - mDoorsType - - - - - - - - - - - - - - - - - - - - - - - Mechanical power - - - - - - - - - - - Mechanical power value [W] - - - - - - - - Torque [Nm] - - - - - - - Force [N] - - - - - - - - - - - - - - - Mechanical power - - - - - - - - - - - Mechanical power value [W] - - - - - - - - Torque [Nm] - - - - - - - Force [N] - - - - - - - - - - - - - - - mElectricalDistributionType - - - - - - - - - - - - - Electrical distribution mass description - - - - - - - - - - - - - - mElectricalGenerationType - - - - - - - - - - - - - Electrical generation mass description - - - - - - - - - - - - - - mEmergencyEquipmentsType - - - - - - - - - - - - - - - - - - - - - - - mEmergencyOxygenSystemsType - - - - - - - - - - - - - - - - - - - - - - - mEmptyULDsType - - - - - - - - - - - - - - - - - - - - - - - mEmptyULDType - - - - - - - - - - - - - - - - - - - - - - Engine APU oils - - - - - - - - - - - - - - Engine APU oil - - - - - - - - - - - - - mEngineControlType - - - - - - - - - - - - - Engine control mass description - - - - - - - - - - - - - - mEquippedEnginesType - - - - - - - - - - - - - - Equipped engines mass description - - - - - - - - - - - - - - - mExtLightingsType - - - - - - - - - - - - - - - - - - - - - - - mFireProtectionType - - - - - - - - - - - - - Fire protection mass description - - - - - - - - - - - - - - mFixedGalleysType - - - - - - - - - - - - - - - - - - - - - - - mFixedLeadingEdgesType - - - - - - - - - - - - - - - - - - - - - - - mFixedLeadingEdgeType - - - - - - - - - - - - - - - - - - - - - - mFixedTrailingEdgesType - - - - - - - - - - - - - - - - - - - - - - - mFixedTrailingEdgeType - - - - - - - - - - - - - - - - - - - - - - - - mFlightControlsType - - - - - - - - - - - - - Flight controls mass description - - - - - - - - - - - - - - mFloorCoveringsType - - - - - - - - - - - - - - - - - - - - - - - mFramesType - - - - - - - - - - - - - - - - - - - - - - - mFreshWaterSystemsType - - - - - - - - - - - - - - - - - - - - - - - mFuelSystemType - - - - - - - - - - - - - Fuel system mass description - - - - - - - - - - - - - - Fuel mass - - - - - - - - - - - - - Fuel mass description - - - - - - - - - - - - - - Mass - - - - - - - - - - - - - Furnishing mass description - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - mFuselagesStructureType - - - - - - - - - - - - - Fuselages structure mass description - - - - - - - - - - - - - - - mFuselageStructureType - - - - - - - - - - - - - Fuselage structure mass description - - - - - - - - - - - - - - - - - - - - - - - - - - mHydraulicDistributionType - - - - - - - - - - - - - Hydraulic distribution mass description - - - - - - - - - - - - - - mHydraulicGenerationType - - - - - - - - - - - - - Hydraulic generation mass description - - - - - - - - - - - - - - In-flight entertainment systems - - - - - - - - - - - - - - - - - - - - - - - mInstrumentPanelType - - - - - - - - - - - - - Instrument panel mass description - - - - - - - - - - - - - - mInsulationsType - - - - - - - - - - - - - - - - - - - - - - - mIntegratedModularAvionicsType - - - - - - - - - - - - - Integrated modular avionics mass description - - - - - - - - - - - - - - mInterGasSystemType - - - - - - - - - - - - - Inter gas system mass description - - - - - - - - - - - - - - Mission definitions - - - - - General description - Specifies mission profiles required for the performance evaluation of air vehicles (aircraft, rotorcraft, etc.). The missionDefininitions node is constructed in such a way, that all civil aircraft missions and missions from MIL-STD-3013A can be specified. - > - - - Hierarchical buildup of the mission definition - - The mission definition is built-up in a hierarchical way. As the topmost element of the hierarchical mission definition, missions are created within the missions node. Here, one or more segmentBlocks are referenced. These again link to a sequence of segments, making up parts of the missions: - - - - - - - <missions> - - - containing the - <startCondition> - and a sequence of - <segmentBlockUIDs> - - - - - <segmentBlocks> - - - - grouping multiple - <segments> - and providing overall information concerning the block of segments: - - - - - constraints in the form of an - endCondition - or given - flightPath - , - - - variableSegments - and the corresponding - variableConditions - in case a segment should be adjusted such to meet the - segmentBlock - 's - endCondition - , - - - fuelPlanningType - ( - designFuel - , - reserveFuel - , - additionalFuel - ), - - - segmentDirection - and - numberOfRepetitions - . - - - - - - - - <segments> - - - - containing detailed information per segment: - - - EITHER - - - - - segmentType - , - - - endConditions - , - - - constraints - , - - - environmentalConditions - - - - - OR - massFraction - - - OR - mass - - - - - - - - startConditions, constraints, endConditions and the relationalOperator attribute - - the startCondition is provided at the mission node. Each subsequent segmentBlock/segment ends by the provided endCondition. - - - - <startCondition> - - start condition of the mission (can be an airfield or mid-air condition) - - - - <endCondition> - - - specific end condition for a - segmentBlock - or - segment - (e.g.: an altitude or velocity) - - - - - <constraint> - - - specific performance settings for a - segmentBlock - or - segment - (e.g.: a cruise Mach number) - - - - - attribute  - @relationalOperator - - - Indicate how conditions should be interpreted: - - - - enum: „lt“, „le“, „eq“, „ne“, „ge“, „gt“ - , - - - Examples: - - - 0.78 -1800 - ]]> - - - - - - - - - - - - - Example implementation for a civil transport mission - - - - - - In the figure above, an example for a civil aircraft transport mission is provided. - - - The mission starts at a position of 0, 0, 0 with 0 velocity, as provided by the - startCondition - of the - mission - node. Furthermore, the environmental conditions are provided: ISA atmosphere with a - deltaTemperature - of 0 [K]. The mission consists of three - segmentBlocks - : a designMission, reserves and the taxiIn - segmentBlock - . - - - - example mission - this is an example mission - - 0.0 - - 0.0 - 0.0 - 0.0 - - - ISA - 0.0 - - - - designMission - reserves - endPhase - - - ]]> - - - The designMission - segmentBlock - is shown below. It provides a set of five segments, together making up a mission with a range of 1000 [nm] or 1852 [km]. The “cruise” segment is the variable segment, which thereby should have a range of: - 1852000 – range(climb) – range(descent) - , provided the taxiOut and takeOff segments are not providing any range credit. The fuel burned during this - segmentBlock - should be added to the - designFuel - , the - segmentDirection - is provided for illustration purposes. - - - - - design mission - segment block for the design mission - - - 1852000 - - - - - cruise - range - - - designFuel - outbound - - taxiOut - takeOff - climb - cruise - descent - - - - - ]]> - - - The first and second segment are providing input for the part of the - segmentBlock - that doesn’t need simulation. During the taxiOut phase, 50 [kg] of fuel is burned. The takeOff phase has a duration of 30 [sec]. - - - - taxi out - taxi out segment - massFraction - 50 - - - take off - take off segment - takeOff - - 00:00:30 - - - ]]> - - - The rest of the segments make-up the flying part of the - designMission - . The climb phase, ending at an altitude of FL330 or 10058.4 [m], provides a constraint-lapse having discrete steps, typical for transport aircraft (a 250 kt / 300 kt / M 0.78 climb profile). Through the - referenceEndconditionUID - “altClimb”, a link to the altitude - endCondition - of the segment at the basis of this climb profile is provided. - - - - - - Altitude from - - - Altitude to - - - calibratedAirspeed - - - machNumber - - - - 0.0 [m] - 0.303 * 10058.4 = 3047.7 [m] - ≤ 128.61 [m/s] - ≤ 0.78 [-] - - - 0.303 * 10058.4 = 3047.7 [m] - 10058.4 [m] - ≤ 154.33 [m/s] - ≤ 0.78 [-] - - - - - The cruise phase is not fixed to a certain altitude and has no - endCondition - , since its range is determined by the - segmentBlock - information. The descent phase makes sure the vehicle lands at an altitude of 0 [m]. In this case, since the values are not explicitly provided, it is up to the mission simulation software to determine, when the cruise phase ends and the descent phase starts. - - - - climb - climb with: speed @ MFCS (set to machNumber le 0.78 [-]), altitude @ FL330 - climb - - - 10058.4 - - - - - altitude - 0.0;0.303 - discrete - 128.61;154.33 - 0.78;0.78 - velocity - - - - - cruise - cruise with: speed @ optimum cruise speed, altitude @ optimum cruise altitude - cruise - - - - descent to MSL - descent to MSL altitude - descent - - - 0 - - - - ]]> - - - Two more - segmentBlocks - make up the mission. The “reserves” - segmentBlock - provides information for the cruise to alternate airport and loitering phase and the corresponding burnt fuel is considered - reserveFuel - . The mission ends with a landing and taxiIn phase within the “endPhase” - segmentBlock - , of which the burnt fuel is considered - additionalFuel - . The following then holds: - blockFuel - = - designFuel - + - additionalFuel - . - - - - - - - - - - - - - - - - - - - - - - - - - - - UID of the runway - - - - - - - Offset from runway threshold in cartesian coordinates in the runway coordinate system - - - - - - - - - - - - - - Setting default and specific performance maps to be used for a model - - - - - - - - - - Default performance map which is used if no other performance map - is assigned through the specificPerformanceMap node - - - - - List of specific performance maps used on dedicated mission segments or pointPerformance requirements - - - - - - - - - - - - - Specific performance settings for the segmentBlock (e.g.: a cruise Mach number) - - - - - - - - - - - - - - - - - - - - Segment blocks - - - A list of segment blocks. A segment block specifies conditions for a predefined combination of segments (e.g.: setting the total range for a block of segments consisting of a takeOff, climb, cruise, descent and landing segment). - - - - - - - - - - - - - - - - - - - Segment block - - - A segment block specifies conditions for a predefined combination of segments (e.g.: setting the total range for a block of segments consisting of a takeOff, climb, cruise, descent and landing segment). - - - - - - - - - - Name - - - - - Description - - - - - - Segment direction. Either 'outbound' or 'inbound'. Only needed for radiusOfAction kind of missions. - - - - - - - - - - - - - - List of segment uID's making up the segmentBlock. These should be ordered, such that the segment connections are correct. - - - - - - - Specifies to which type of mass the segment fuel mass - should be added (blockFuel = designFuel + additionalFuel; Total fuel requirement - = blockFuel + reserveFuel; designFuel = the fuel of the segmentBlock is part of the design mission) - - - - - - - - - - - - - - - - Number of repetitions of this segment block, e.g. to perform repeated holding patterns - - - - - - - - - - - - - - - - End condition - - - - - Specifies the end conditions for a segment or segment block (e.g.: an altitude or velocity). If a phase has no endCondition, it will base its endCondition on the segmentBlock settings (e.g.: it is the cruise segment, retrieving its total length based on the length of the segmentBlock minus all other segment lengths available within the segmentBlock). - - - - - - - - - - - - - - Calibrated airspeed at the end of the segment [m/s] - - - - - - - - - - - - - - Mach number at the end of the segment - - - - - - - - - - - - - - - Position at the end of the segment in xyz coordinates - - - - - - - Position at the end of the segment in geo coordinates - - - - - - - - Reference to the runway on which the segment ends - - - - - - - - - - - - - - - - massFraction ending the segment [-] - - - - - - - - - - - - - - massFraction of remaining fuel ending the segment [-] - - - - - - - - - - - - - - Absolute mass of remaining fuel ending the segment [kg] - - - - - - - - - - - - - - Consumed fuel ending the segment [kg] - - - - - - - - - - - - - - Power fraction of remaining at the end of the segment - - - - - - - - - - - - - - Absolute power left ending the segment [W] - - - - - - - - - - - - - - Consumed power ending the segment [W] - - - - - - - - - - - - - - - - Flight heading at the end of the segment in compassAngle with reference to true North [deg] - - - - - - - - - - - - - - Total change of heading angle during segment (a full turn is 360 degrees) [deg] - - - - - - - - - - - - - - - Flown distance ending the segment - - - - - - - - - - - - - - - Duration of the segment [hh:mm:ss] - - - - - - - - - - - - - - UTC time at end of segment [hh:mm:ss] - - - - - - - - - - - - - - - Specific excess power at the end of the segment - - - - - - - - - - - - - - Rate of climb ending the segment [m/s] - - - - - - - - - - - - - - Achieved flightPathAngle ending the segment [deg] - - - - - - - - - - - - List of stores released in the segment. The corresponding weightAndBalance vector for retrieving the new state as well as a potential change in aerodynamicPerformanceMap (if external stores are released) should be reflected within the configuration node at model level. - - - - - - - - - - - - - - Mission segments - - - A collection of mission segments which can be reused to define missions. - - - - - - - - - - - - - - - - - - - Segment - - - Definition of a mission segment which can be used to define missions. - - - - - - - - - - Name - - - - - Description - - - - - Type of the mission segment (takeOff, clime, cruse, ...) - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Indication whether the distance flown during the segment is to be taken into account in the segmentBlock's distance calculation. - - - - - - Environmental conditions. If the environmentalCondition is not provided at segment level, the conditions of the - previous segment are inherited (this inheritance can continue until the startCondition, where the initial - environmentalConditions are provided). - - - - - - - Fuel mass - - - - - - - - - - - - - - - - - - - - Start conditions - - - Conditions which define the start of a mission - - - - - - - - - - - Calibrated airspeed at the start of the mission [m/s] - - - - - Mach number at the start of the mission - - - - - - - Global coordinate at the start of the mission in xyz coordinates - - - - - Global coordinate at the start of the mission in geographic coordinates (longitude, latitude, altitude) - - - - - - UID of the runway at which the - mission starts - - - - - - - - Flight heading at the start of the mission, in compassAngle with reference to true North - - - - - - UTC time at start of mission - - - - - - - - - - - - - - - - UID of the runway - - - - - - - Offset from runway threshold in the runway coordinate system - - - - - - - - - - - - - - Missions - - - A list of missions. - - - - - - - - - - - - - - - - - - - Mission - - - Contains a list of segmentBlock uID's forming the mission along with additional mission information. - - - - - - - - - - Name - - - - - Description - - - - - - - List of segmentBlock uID's forming the mission. Segments must first be grouped in segmentBlocks to be assigned to a mission. - - - - - - - - - - - - - - - mLandingGearsType - - - - - - - - - - - - - - Landing Gears mass description - - - - - - - - - - - - - - - mLandingGearSupportsType - - - - - - - - - - - - - - - - - - - - - - - mLandingGearType - - - - - - - - - - - - - - Landing Gear mass description - - - - - - - - - - - - - - - - - - - - - - mLavatoriesType - - - - - - - - - - - - - - - - - - - - - - - mLiningsType - - - - - - - - - - - - - - - - - - - - - - - Mass - - - - - - - - - - - - - Manufacturer empty mass description - - - - - - - - - - - - - - - - - - mMillitarySystemsType - - - - - - - - - - - - - Military systems mass description - - - - - - - - - - - - - - mMoveableLeadingEdgesType - - - - - - - - - - - - - - - - - - - - - - - mMoveableLeadingEdgeType - - - - - - - - - - - - - - - - - - - - - - - - mMoveablesType - - - - - - - - - - - - - - - - - - - - - - - - mMoveableTrailingEdgeType - - - - - - - - - - - - - - - - - - - - - - - - mNavigationType - - - - - - - - - - - - - Navigation mass description - - - - - - - - - - - - - - Monetary values - - - - - - - - - - - - - - - - - - - - - - - Mass - - - - - - - - - - - - - Operator items mass description - - - - - - - - - - - - - - - - - - - - - - - - - - - - mOverheadBinsType - - - - - - - - - - - - - - - - - - - - - - - mPartStowDoorsType - - - - - - - - - - - - - - - - - - - - - - - mPassengersType - - - - - - - - - - - - - - - - - - - - - - - mPassengerType - - - - - - - - - - - - - - - - - - - - - - Passengers masses - - - - - - - - - - - - - Passanger masses Description - - - - - - Passanger mass Description - - - - - - - - - - - - - - Payload mass - - - - - - - - - - - - - Payload mass description - - - - - - - - - - - - - - - Pintle struts - - - - - - - - - - - - - - Pintle struts mass description - - - - - - - - - - - - - - - Mass - - - - - - - - - - - - - Power units mass description - - - - - - - - - - - - - - - - - - - - mPylonAttachmentsType - - - - - - - - - - - - - - - - - - - - - - - mPylonsType - - - - - - - - - - - - - - Pylons mass description - - - - - - - - - - - - - - - Removable crew rests - - - - - - - - - - - - - - Removable crew rest - - - - - - - - - - - - - mRibsType - - - - - - - - - - - - - - - - - - - - - - - mRibType - - - - - - - - - - - - - - - - - - - - - - mSeatsType - - - - - - - - - - - - - - - - - - - - - - - mShellsType - - - - - - - - - - - - - - - - - - - - - - - - mShellType - - - - - - - - - - - - - - - - - - - - - - - - - Side Struts - - - - - - - - - - - - - - Side struts mass description - - - - - - - - - - - - - - - mSkinPanelsType - - - - - - - - - - - - - - - - - - - - - - - mSkinsType - - - - - - - - - - - - - - - - - - - - - - - mSparCellsType - - - - - - - - - - - - - - - - - - - - - - - mSparSkinsType - - - - - - - - - - - - - - - - - - - - - - - mSparsType - - - - - - - - - - - - - - - - - - - - - - - mSparType - - - - - - - - - - - - - - - - - - - - - - - - mSpecialStructuresType - - - - - - - - - - - - - - - - - - - - - - - mSpoilersType - - - - - - - - - - - - - - - - - - - - - - - mStringersType - - - - - - - - - - - - - - - - - - - - - - - Mass - - - - - - - - - - - - - Structure mass description - - - - - - - - - - - - - - - - - Mass - - - - - - - - - - - - - Systems mass description - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Toilet fluids - - - - - - - - - - - - - - Toilet fluid - - - - - - - - - - - - - mTrailingEdgeDevicesType - - - - - - - - - - - - - - - - - - - - - - - mTrailingEdgeDeviceType - - - - - - - - - - - - - - - - - - - - - - - - mULDContentsType - - - - - - - - - - - - - - - - - - - - - - - mULDContentType - - - - - - - - - - - - - - - - - - - - - - UnusableFuels - - - - - - - - - - - - - - Unusable fuel - - - - - - - - - - - - - mVacuumWasteSystemsType - - - - - - - - - - - - - - - - - - - - - - - mWallsType - - - - - - - - - - - - - - - - - - - - - - - mWasteWaterSystemsType - - - - - - - - - - - - - - - - - - - - - - - Water reservoirs - - - - - - - - - - - - - - Water reservoir - - - - - - - - - - - - - Wheels - - - - - - - - - - - - - - Wheels mass description - - - - - - - - - - - - - - - mWindowsType - - - - - - - - - - - - - - - - - - - - - - - mWingBoxType - - - - - - - - - - - - - - - - - - - - - - - - - mWingsStructureType - - - - - - - - - - - - - Wings structure mass description - - - - - - - - - - - - - - - mWingStructureType - - - - - - - - - - - - - Wing structure mass description - - - - - - - - - - - - - - - Center cowl - - - - - The - centerCowl - is defined by the rotation of a given curve profile (referenced via - curveUID - ) around the - x - -axis. - - - - - - - - - - - - - - - Offset of the rotation curve in x-direction - - - - - UID of the curve profile (vehicles/profiles/curveProfiles/..) - - - - - - - - - - - - - - Nacelle cowl - - - - Describes the cowl geometry for nacelles - using sections positioned around the - rotational center of the engine. - - - - - - - - - - - - - - - - - - - - - - - Guide curves - - - - - - - - - - - - - - - - - - - Guide curve - - - - - The following figure shows the basic setup of the guide curves. - They always start at a given ζ-position ( - fromZeta - ) on the profile of the specified start section ( - startSectionUID - ) and end at the ζ-position ( - toZeta - ) on the profile of the subsequent section. - The relative coordinates of the guide curves are specified in - cpacs/vehicles/profiles/guideCurves - and referenced via its - uID - . - - - - - - Note - : Guide curves and profiles must result in a valid curve network. - - - The guide curve points are interpreted as ( - Δr - and - Δx - ) offsets from a cubic polynomial. - This polynomial serves as a baseline for guide curves between segments located on different radial positions with smooth transitions: - - - - - - Note - : Currently, the nacelles do not have an explicit guide curve type but employ the standard guide curve definition, which is used in wings and profiles. - Therefore, the parameters have a different meaning: - - - - Standard guide curve parameter - Nacelle guide curve equivalent - Description - - - rX - - φ - - - Independent variable normalized to - [0,1] - - - - rY - - Δx - - - Orthogonal offset (translation in - x - -direction) - - - - rZ - - Δr - - Radial offset - - - - - - - - - - - - - - Name - - - - - - - Description - - - - - - - UID of the guide curve profile - - - - - - - UID of the start section - - - - - - - Curve coordinate of the referenced section profile at which the guide curve shall start. - Valid values are in the interval -1,..,1. - - - - - - - Curve coordinate of the profile following the referenced section profile. - It defines where the guide curve ends. - Valid values are in the interval -1,..,1. - - - - - - - - - - - - - - nacelleProfilesType - - - Nacelle profiles type, containing nacelle profile geometries. - See profileGeometryType for further documentation - - - - - - - - - - - - - - - - - - - Sections - - - - - - - - - - - - - - - - - - - - - - Section - - - - - An engine nacelle is defined by sections, where at least one and up to an infinite number of sections can be specified. - Lofting of the nacelle surface along the sections is done in cylindrical coordinates. - The - coordinate origin refers to the center of the fan - , i.e. the sections and their profiles are typically shifted in negative x-direction. - - - Note - : In the current CPACS release, transformations are still labeled as Cartesian coordinates. - It is current work in progress to explicitly introduce cylindrical coordinates. - Until this is implemented in a future CPACS release, the implicit conventions listed below apply: - - - - Translation component - Cylindrical coordinate equivalent - Description - - - - x - - - ϑ - - - Rotation angle around - x - - - - - y - - - h - - Horizontal translation - - - - z - - - r - - Radial translation - - - - The following example illustrates the setup of a nacelle with 4 sections. - These are rotated by 0, 120, 180 and 240 degrees around the - x - -axis (given by - translation/x - ). - To illustrate the possible transformations, the profile of the upper section is shifted slightly further in the negative - x - -direction ( - translation/y - ), while the lower section has a smaller radial distance from the rotation axis ( - translation/z - ). - In addition, the sections are scaled differently ( - transformation/scaling - ; not shown in the example figures) in order to create a straight trailing edge and to realize a flattened profile near the ground. - - - The following example also shows the profile cut-outs due to the radially symmetric inner region of the nacelle defined by the - rotationCurve - . For detailed information, please refer to the documentation of the - rotationCurve - element. - - - - - - The first section is not rotated ( - x=ϑ=0 - ), but shifted vertically in negative direction ( - y=h=-0.257 - ). - The radial distance is given by - z=r=0.365 - : - - - - Upper section - - - 1.055 - 1 - 1 - - - 0.0 - -0.257 - 0.365 - - - fanCowlUpperSectionProfile - - ]]> - - - The second section is rotated around the - x - -axis ( - x=ϑ=120 - ) as well as scaled by a factor of 1.1 in its profile height: - - - - Inboard section - - - 1 - 1 - 1.1 - - - 120.0 - -0.2 - 0.365 - - - fanCowlUpperSectionProfile - - ]]> - - - The third section is rotated around the - x - -axis by 180° and scaled by a factor of 0.8 in its profile height: - - - - Lower section - - - 1 - 1 - 0.8 - - - 180.0 - -0.2 - 0.33 - - - fanCowlUpperSectionProfile - - ]]> - - - - - - - - - - - - Name - - - - - Description - - - - - - UID of the profile - - - - - - - - - - - - - - Noise - - - - - - - - - - - - - FAR approach noise level - - - - - FAR sideline noise level - - - - - FAR take-off noise level - - - - - - - - - - - - - Nose landing gears - - - List of nose gears - - - - - - - - - - - - - - - - - - - Operating empty mass - - - - - - - - - - - - - Operating empty mass description - - - - - - - - - - - - - - - - operationalCasesType - - - - - - - - - - - - - - - - - - - - - - operationalCaseType - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Operation Limit Increments - - - Changes of the deltas of operation limit angles with respect to the corresponding increment aeroPerformanceMaps. - Values are specified as an array with same indices like the corresponding increment map. - - - - - - - - - - Minimum delta angle of attack [deg] - - - - - Maximum delta angle of attack [deg] - - - - - - - - - - - - - - Orthotropic material properties for 2D materials - - - - - Defines the material properties for an orthotropic material in the plane stress state (i.e., shell). The strain-stress relationship is defined as: - - - - Inverting the strain-stress relation and introducing thermal expansion yields: - - - - with: - - - - The terminology refers to the following literature: - - [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. - - - - - - - - - - - - Young's modulus in material direction 1 [N/m^2] - - - - - Young's modulus in material direction 2 [N/m^2] - - - - - Shear modulus in material in 2-3 plane [N/m^2] - - - - - Shear modulus in material in 3-1 plane [N/m^2] - - - - - Shear modulus in material in 1-2 plane [N/m^2] - - - - - Poisson's ratio - - - - - Thermal expansion coefficient in material direction - 1 [1/K] - - - - - Thermal expansion coefficient in material direction - 2 [1/K] - - - - - Thermal conductivity of the material in material direction 1 [W/(m*K)] - - - - - - Thermal conductivity of the material in material direction 2 [W/(m*K)] - - - - - - Allowable stress for tension in material direction 1 - [N/m^2] - - - - - Allowable stress for compression in material - direction 1 [N/m^2] - - - - - Allowable stress for tension in material direction 2 - [N/m^2] - - - - - Allowable stress for compression in material - direction 2 [N/m^2] - - - - - Allowable stress for shear [N/m^2] - - - - - - Allowable strain for tension in material direction 1 - - - - - - Allowable strain for compression in material - direction 1 - - - - - Allowable strain for tension in material direction 2 - - - - - - Allowable strain for compression in material - direction 2 - - - - - Allowable strain for shear - - - - - - - - - - - - - - Orthotropic material properties for 3D materials - - - - - Defines the material properties for an elastic orthotropic material in three spatial directions (i.e., solid). The strain-stress relationship is defined as: - - - - Note that nuij is related to nuji by: - - - - The terminology refers to the following literature: - - [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. - - - - - - - - - - - - Young's modulus in material direction 1 [N/m^2] - - - - - Young's modulus in material direction 2 [N/m^2] - - - - - Young's modulus in material direction 3 [N/m^2] - - - - - Shear modulus in the 2-3 plane [N/m^2] - - - - - Shear modulus in the 3-1 plane [N/m^2] - - - - - - Shear modulus in the 1-2 plane [N/m^2] - - - - - Poisson's ratio in in 2-3 plane - - - - - Poisson's ratio in in 3-1 plane - - - - - Poisson's ratio in in 1-2 plane - - - - - Thermal expansion coefficient in material direction - 1 [1/K] - - - - - Thermal expansion coefficient in material direction - 2 [1/K] - - - - - Thermal expansion coefficient in material direction - 3 [1/K] - - - - - Thermal conductivity of the material which couples heat flux in material direction 2 with temperature gradient in material direction 3 [W/(m*K)] - - - - - Thermal conductivity of the material which couples heat flux in material direction 3 with temperature gradient in material direction 1 [W/(m*K)] - - - - - - Thermal conductivity of the material which couples heat flux in material direction 1 with temperature gradient in material direction 2 [W/(m*K)] - - - - - - Allowable stress for tension in material direction 1 - [N/m^2] - - - - - Allowable stress for compression in material - direction 1 [N/m^2] - - - - - Allowable stress for tension in material direction 2 - [N/m^2] - - - - - Allowable stress for compression in material - direction 2 [N/m^2] - - - - - Allowable stress for tension in material direction 3 - [N/m^2] - - - - - Allowable stress for compression in material - direction 3 [N/m^2] - - - - - Allowable stress for shear in 2-3 plane [N/m^2] - - - - - - Allowable stress for shear in 3-1 plane [N/m^2] - - - - - Allowable stress for shear in 1-2 plane [N/m^2] - - - - - - Allowable strain for tension in material direction 1 - - - - - - Allowable strain for compression in material - direction 1 - - - - - Allowable strain for tension in material direction 2 - - - - - - Allowable strain for compression in material - direction 2 - - - - - Allowable strain for tension in material direction 3 - - - - - - Allowable strain for compression in material - direction 3 - - - - - Allowable strain for shear in 1-3 plane - - - - - - Allowable strain for shear in 1-3 plane - - - - - - Allowable strain for shear in 1-2 plane - - - - - - - - - - - - - - outerCutOutProfileType - - - - - - - - - - - - - - - - - - - - - - - Container for parameter definitions - - - Contains a of the design parameter definitions. - - - - - - - - - - - - - - - - - - - - Parameter definition for design studies. - - - Contains a name for the design parameter to give semantic meaning to parameters used in design studies. - - - - - - - - - - - Name of parameter - - - - - - - - - - - - - - paxCrossBeamsAssemblyType - - - PaxCrossBeamsAssembly type, containing pax crossBeam - assemblies - - - - - - - - - - - - - - - - - - - paxCrossBeamStrutsAssemblyType - - - PaxCrossBeamStrutsAssembly type, containing pax - crossBeam strut assemblies - - - - - - - - - - - - - - - - - - - paxDoorsAssemblyType - - - PaxDoorsAssembly type, containing pax door assemblies - - - - - - - - - - - - - - - - - - - - payloadGlobalType - - - - - - - - - - - - - - - - - - - - - - - Selection of performance maps - - - - - - - - - - Engine performance map selection - - - - - Aerodynamic performance map selection - - - - - - - - - - - - - Configurations which apply for this performance requirement - - - - - - - - - - - - - - - - Default configuration uID - - - - - - - - - - - - - - - Performance requirements - - - - - - - - - - - - - - - - - - - - - - - - - - performanceTargetsGlobalType - - - - - - - - - - - - - - - - - - - - - - - - - - - - Multi-phase mass flow - - - - - - - - - - - Pressure - - - - - - - Temperature - - - - - - - - - - - - - - - Multi-phase mass flow - - - - - - - - - - - Pressure - - - - - - - Temperature - - - - - - - - - - - - Pintle strut(s) (Assumption: one end of the strut will connect to the main strut and the other end will be given as endPoint) - - - - - Pintle strut (one or two pintle struts are supported) - - - - - - - - - - - Piston - - - - - Geometric description and material properties of the - landing gear piston. The figure below shows the condition of the - uncompressed piston, where the length of the exposed part is the - sum of the - maxSpringDeflection - and the - compressedExternalLength - : - - - - - - - - - - - - - - - Length of the piston - - - - - - Maximum spring deflection of the piston (difference between minimum and maximum deflection) - - - - - Length of the piston that remains outside of the main strut in fully compressed state - - - - - - - - - - - - - - Points on plasticity curve of material - (min. 1 point) - - - - - - - - - - - - plasticityCurvePointType - - - - - - - - - - - - - Tangent modulus [N/m^2] - - - - - True stress [N/m^2] - - - - - - - - - - - - - plasticityCurvesType - - - - - - - Plastification curve incl. element elimination (isotropic - materials). The data may be used to describe the plastic behavior of isotropic - materials in non-linear analysis, such as crash simulations. The input is defined - according to the needs of Material 103 (single stress strain option) in the - PAM-CRASH explicit Finite Element code, but can also be used for equivalent material - laws in alternative simulation environment (see PAM-CRASH Solver Reference Manual., - Material 103). - - - - - - - - - - - - - - - - This type describes the plasticity curve of isotropic - materials - - - - ... - - Plastification curve incl. element elimination - (isotropic materials) - - Plastification curve incl. element elimination (isotropic - materials) The data may be used to describe the plastic behavior of - isotropic materials in non-linear analysis, such as crash - simulations. The input is defined according to the needs of Material - 103 (single stress strain option) in the PAM-CRASH explicit Finite - Element code, but can also be used for equivalent material laws in - alternative simulation environment (see PAM-CRASH Solver Reference - Manual., Material 103) - Source: PAM-CRASH V2010 - Notes Manual - - - - - - - - - - - - Name of the post failure definition - - - - - - - Description of the post failure - definition - - - - - - - Strain rate for following plastcity - curve [1/s] - - - - - - - - plasticEliminationStrain [-]; Plastic - strain for element elimination during - the non-linear analysis - - - - - - - - - - - - - - Point with global/local reference - - - PointAbsRel type, containing an xyz data triplet. Each - of the components is optional. The refType attribute defines, - whether coordinates are absolute in the global coordinate system - [absGlobal], absolute in the parent element's local coordinate - system [absLocal]. If the object does not have a - parent, only [absGlobal] is permitted. - - - - - - - - - - X-Component - - - - - Y-Component - - - - - Z-Component - - - - - - - - - - Absolute values in global coordinate system - - - - - Absolute values in local coordinate system (default) - - - - - - - - - - - - - - - Point with constraints - - - Point constraint type, containing an xyz data triplet. - - - - - - - - - - X-Component - - - - - Y-Component - - - - - Z-Component - - - - - - - - - - - - - List of 3D points, kept in three relative coordinate - vecors (rX, rY, rZ) - - - - This set of vectors contains an ordered list of points - for rX, rY, and rZ coordinates in the form of stringBased - Vectors. The x, y and z vector elements with the same index - specify a 3D point relative to a geometric segment. - - - - - - - - - - - - - - - - - - - - Vector of rX coordinates. Relative - circumferential coordinate on wing, fuselage or nacelle profile - - - - - - Vector of rY coordinates. Relative span - coordinate along a segment - - - - - Vector of rZ coordinates. Relative coordinate - normal to the linear strake (normalised with chordlength / - diameter c*) - - - - - - - - - - - - - List of points - - - PointList type, containing an ordered list of points - - - - - - - - - - - Data point - - - - - - - - - - - - - List of points in x,y - - - PointList type, containing an ordered list of points - - - - - - - - - - - Data points in x-y-space. - - - - - - - - - - - - - List of 2D points, kept in two coordinate vecors (x, y) - - - - This set of vectors contains an ordered list of points - for x and y coordinates in the form of stringBased Vectors. - The x and y vector elements with the same index specify a 2D - point. The coordinates of the x vector of [0, 1]. - - - - - - - - - - - Vector of x coordinates - - - - - Vector of y coordinates - - - - - - - - - - - - - List of 3D points, kept in three coordinate vecors (x, - y, z) - - - - This set of vectors contains an ordered list of points - for x, y and z coordinates in the form of stringBased Vectors. - The x, y and z vector elements with the same index specify a 3D - point. - - - - - - - - - - - Vector of x coordinates - - - - - Vector of y coordinates - - - - - Vector of z coordinates - - - - - - - - - - - - - - Constraints - - - - Constraint settings for the point performance definition - - - - - - - - - - - Calibrated airspeed [m/s] - - - - - - - Mach number [-] - - - - - - - Climb angle [deg] - - - - - - - Rate of climb [m/s] - - - - - - - Rate of turn [deg/s] - - - - - - Thrust setting for derated engine as fraction of max. thrust (e.g.: for powered descents, deceleration not at IDLE, manoevres) - - - - - - - Rate of velocity [m/s^2] - - - - - - - Duration [s] - - - - - - - Angle of attack [deg] - - - - - - - Constant altitude [m] - - - - - - - - - - - - - - Point performance definitions - - - List of point performance definitions - - - - - - - - - - - - - - - - - - - pointPerformanceType - - - Specific performance settings for the point performance calculation (e.g.: a cruise Mach number) - - - - - - - - - - Name - - - - - Description - - - - - - - Defines at which part of the mission - the point performance should be - considered - after indicated segment - of the mission as defined in - performanceCase - - - - - - - Defines at which part of the mission - the point performance should be - considered - at the defined - massFraction within the mission as - defined in performanceCase - (mCurrent/mTO) - - - - - - - Defines at which part of the mission - the point performance should be - considered - at the defined - fuelFraction within the mission as - defined in performanceCase - (mFuelCurrent/mFuelTO) - - - - - - - - Indicates the type of point performance - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Requirements - - - - Requirement settings for the point performance definition - - - - - - - - - - - Sustained load factor to be achieved - - - - - - - Instantaneous load factor to be achieved - - - - - - - Specific excess power to be achieved [m/s] - - - - - - - Roll rate to be achieved [deg/s] - - - - - - - Roll acceleration to be achieved upon control onset [deg/s^2] - - - - - - - Roll acceleration to be achieved upon control stop [deg/s^2] - - - - - - - - - - - - - - Point: x,y,z - - - Point type, containing an xyz data triplet. - - - - - - - - - - X-Component - - - - - Y-Component - - - - - Z-Component - - - - - - - - - - - - - - Point: x - - - Point type, containing a x data. - - - - - - - - - - X-Component - - - - - - - - - - - - - - Point: x,y - - - Point type, containing an xy data doublet. - - - - - - - - - - X-Component - - - - - Y-Component - - - - - - - - - - - - - - Point: x,y,z - - - Point type, containing an obligatory xyz data triplet. - - - - - - - - - - X-Component - - - - - Y-Component - - - - - Z-Component - - - - - - - - - - - - - - Point: x, z - - - Point type, containing an xz data doublet. - - - - - - - - - - X-Component - - - - - Z-Component - - - - - - - - - - - - - - Point: y - - - Point type, containing a y data. - - - - - - - - - - Y-Component - - - - - - - - - - - - - - Point: y, z - - - Point type, containing an yz data doublet. - - - - - - - - - - Y-Component - - - - - Z-Component - - - - - - - - - - - - - - Point: z - - - Point type, containing a z data. - - - - - - - - - - Z-Component - - - - - - - - - - - - - - Positive double values larger than 0 - - - - - - - - - - - - - - - - - Positive integer values larger than 0 - - - - - - - - - - - - - - - - - Vector with semicolon separated positive integer values - - - - Any positive integer values separated by semicolons are permitted, e.g.: - -<intVectorTest>0;1;2;3;4;5</intVectorTest> - - -<intVectorTest>1</intVectorTest> - - -<intVectorTest>0,1,2,3,4,5</intVectorTest> - - -<intVectorTest>0.;1.;2.</intVectorTest> - - -<intVectorTest>-1;0;1</intVectorTest> - - - - - - - - - - - - - - - - - - - Positionings of the wing. - - - Positionings type, containing all the positionings of - the wing sections. - - - - - - - - - - - - - - - - - - - Positioning of the wing section - - - - The positionings describe an additional translation of - sections. Basically, the positioning is a vector having the - length 'length' and an orientation that is described by the - parameters 'sweepAngle' and 'dihedralAngle'. If the 'sweepAngle' - and the 'dihedralAngle' are set to zero (or left blank) the - positioning vector equals the positive y-axis of the coordinate - system (in case of a positive 'length'). - If the parameter 'fromSectionUID' is set, the - positioning describes the translation between the 'from' towards - the 'to' section. If the parameter 'fromSectionUID' is left - blank the origin of the positioning vector is the origin of the - parent coordinate system. - The origin of the section coordinate system is the - position which is described by the positioning vector PLUS the - translation which is described in the section. - Please note: If the origin of the positioning vector is - defined by using another section, i.e. fromSection is defined, - the origin of this vector equals the end of the positioning - vector of the previous section. This means that the section - translation of the from-section has no influence on the - positioning of the to-section. Therefore the total translation, - which is described by positionings, is the sum of the current - positioning and all positionings that are defined 'before'. - - An example for this is given at positioning 3 and 4 at - the picture below. Please note, that any other combination of - positionings would be possible. - Application of the sweepangle does not lead to a - rotation of the section. Application of the dihedral does not - lead to a rotation of the section. - - - - - - - - - - - - - - Name of the positioning. - - - - - Description of the positioning. - - - - - - Distance between inner and outer section - (length of the positioning vector). - - - - - Sweepangle between inner and outer section. - This angle equals a positive rotation of the positioning vector - around the z-axis of the wing coordinate system. - - - - - - Dihedralangle between inner and outer section. - This angle equals a positive rotation of the positioning vector - around the x-axis of the wing coordinate system - - - - - - Reference to starting section of the - positioning vector. If missing, the positioning is made from the - origin of the wing coordinate system. - - - - - Reference to ending section (section to be - positioned) of the positioning vector. - - - - - - - - - - - - - - Specification of the power breakdown case - - - - - - - - - - - - - Altitude - - - - - - - - Mach number - - - - - - - Calibrated air speed - - - - - - - True air speed - - - - - - - - - - UID of global flight point at cpacs/vehicles/flightPoints/flightPoint - - - - - - - - Configuration - - - - - - - - - - - - - - Power breakdowns - - - - - - - - - - - - - - - - - - - - Specification of the power breakdown case - - - - - - - - - - UID of the corresponding trajectory - - - - - - - - - - - - - Power flow - - - - - - - - - - - Name - - - - - - - Description - - - - - - - UID of the system architecture connection - - - - - - - - - - - - - - Power flow - - - - - - - - - - - - - - - - - - - - - - Power flow - - - - - - - - - - - - - - - - - - - - - - pressureBulkheadAssemblyPositionType - - - PressureBulkheadAssemblyPosition type, containing a - pressure bulkhead assembly position - - - - - - - - - - Frame to which bulkhead is attached to - - - - - - UID of bulkhead element description - - - - - - - - - - - - - - - pressureBulkheadAssemblyType - - - PressureBulkheadAssembly type, containing pressure - bulkhead assemblies - - - - - - - - - - - - - - - - - - - pressureBulkheadsType - - - PressureBulkheads type, containing pressure bulkheads - - - - - - - - - - - - - - - - - - - - pressureBulkheadType - - - PressureBulkhead type, containing data of a pressure - bulkhead - - - - - - - - - - Name of the pressure bulkhead structural - element - - - - - Description of the pressure bulkhead - structural element - - - - - UID of structural sheet element used for the - bulkhead - - - - - Choice between flat and curved bulkhead types - - - - - additional data for flat (forward) pressure - bulkhead - - - - Number of vertical reinforcements on flat - bulhhead - - - - - UID of structural elements used as vertical - reinforcements - - - - - Number of horizontal reinforcements on flat - bulhhead - - - - - UID of structural elements used as - horizontal reinforcements - - - - - - additional data for curved (rear) pressure - bulkhead - - - - Radius of bulkhead calotte in the plane of - the adjacent frame - - - - - maximum flection of the pressure bulkhaed - calotte - - - - - Number of radial reinforcements (equally - distributed) on curved bulhhead - - - - - UID of structural elements used as radial - reinforcements on curved bulkheads - - - - - - - - - - - - - - - - structuralElementType - - - profileBasedStructuralElements type, containing a list - of profile based structural elements - - - - - - - - - - - - - - - - - - - Structural elements based on profiles - - - - - Short description - - The ProfileBasedStructuralElement type containins the - data of a structural element, that are based on 2-dimensional profiles. - - There are three approaches to model profile based structural elements: - - by specifying global beam properties - by referencing a structuralProfile2D element - by choosing one of the prescribed standard profiles - - - - - - 1. Global beam properties - - - In the section - globalBeamProperties - the properties - of the structural profile in an equivalent beam representation - are defined. - - - - - 2. Structural 2D profile - - - The - structuralProfileUID - element refers to the - uID - of the - structuralProfile2D - element. - As described in the corresponding documentation, this profile is defined by several points in the x-y-space. - Two points always form a sheet. - The properties of each sheet are defined in the - sheetProperties - element. - The orthotropy direction of composite materials equals the sheets' x-axis. - The orthotropy direction angle equals a positive rotation around the sheets' z-axis as indicated in the picture below (part 3), which shows an example of a wing stringer.: - - - - - - - - 3. Standard structural 2D profile - - - Instead of referencing a - structuralProfile2D - element, it is also possible to select a predefined standard profile. - These profiles are listed in the figure below. - Under - sheetProperties - , only the - standardProfileSheetID - (equals S1, S2, ...) must now be specified along with a corresponding length. - - - - - - - - - - - - - - - - - Name of the profile based structural element - - - - - - Description of the profile based structural - element - - - - - Choice between global beam properties and sheet properties - - - - - - Choice between general profile element - description (referencing a structuralProfile) and predefined - standard profiles - - - - Definition based on structuralProfile - definition - - - - Reference to the structural profile profile - uID - - - - - - Reference point in structural profile - definition for structural element definition - - - - - - - Standard Profile Type, see picture below for - further information. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - profileGeometry2DType - - - - A profile is defined by a profile name, an optional - description and a 2-dimensional pointlist with both - coordinates mandatory. All point coordinates are transferred - to the global coordinate system depending on the context they - are used in. The points have to be ordered in a mathematical - positive sense. The x-coordinates of the profile has to be - normalized between 0 and 1. First and last point - may, but need not to, be identical. Hence, it is possible to - include "open" profiles. However, the trailing edge position of - the upper and lower point need to be identical. No crooked - trailing edges are possible. - Example 1: For a conventional nacelle profile, the airfoil - coordinates are defined in x and y. The points have to be ordered - from the trailing edge along the lower side to the leading - edge and then along the upper side back to the trailing edge. - When used for a nacelle the profile axis align - with the global axes as follows: - +x_profile -> +x_global; - +y-profile -> -z_global - Example 2: For a fuselage, the coordinates are - also given in x and z with x as the normalized fuselage height. - Starting point of the profile should be the lowest point - (typically in the symmetry plane), then upwards on the positive x-side up to the highest - point (again, typically in the symmetry plane). Depending on, - whether the fuselage shall be specified with symmetry condition - or not, the profile either ends there, or continues on the - negative x-side back down to the lowest point. - Alternatively, it is possible to specify the - coordinates of a profile via the CST (class function /shape - function transformation technique) notation. Please see the - cst2DType for further information. - A profile can be symmetric. In that case the profile - is interpreted as being not closed and will be closed by - mirroring it on the symmetry plane. - - - - - - - - - - - Name of profile - - - - - Description of profile - - - - - - - - - - - - - - - - - - - - - - - - - - - - profileGeometryType - - - - A profile is defined by a profile name, an optional - description and a 3-dimensional pointlist with all three - coordinates mandatory. For typical profiles, one of the - coordinate vectors contains only "0" entries. All point - coordinates are transferred to the global coordinate system. The - points have to be ordered in a mathematical positive sense. - Normalized coordinates are not required. First and last point - may, but need not to, be identical. Hence, it is possible to - include "open" profiles. However, the trailing edge position of - the upper and lower point need to be identical. No crooked - trailing edges are possible. - Example 1: For a conventional wing, the airfoil - coordinates are defined in x and z with all the y-coordinates - set to "0". The points have to be ordered from the trailing edge - along the lower side to the leading edge and then along the - upper side back to the trailing edge. - Example 2: For a fuselage, the coordinates are - typically given in y and z with x set to "0". Starting point of - the profile should be the lowest point (typically in the symmetry - plane), then upwards on the positive y-side up to the highest - point (again, typically in the symmetry plane). Depending on, - whether the fuselage shall be specified with symmetry condition - or not, the profile either ends there, or continues on the - negative y-side back down to the lowest point. - Alternatively, it is possible to specify the - coordinates of a profile via the CST (class function /shape - function transformation technique) notation. Please see the - cst2DType for further information. - A profile can be symmetric. In that case the profile - is interpreted as being not closed and will be closed by - mirroring it on the symmetry plane. - - - - - - - - - - - Name of profile - - - - - Description of profile - - - - - - - - - - - - - - - - - - - - Profiles - - - Profiles type, containing profile geometries - - - - - - - - - - - - - - - - - - - - - - - - - - Attachments of the pylon to the parent. - - - - - - - - - - - - - - - - - - - - - - - Attachment of the pylon to the parent. - - - - - - - - - - - - - Material properties of the attachment. - - - - - - Link to the structural profile of the - attachment. - - - - - - UID of the attachment. - - - - - - - - - - - - Structural properties of the pylon box (ribs, upper, - lower and side panels). - - - - - - - - - - - - - - - - - - - UID of the pylon box. - - - - - - - - - - - - Definition of pylon pins. - - - - - - - - - - - - - - - - - - - - - - Definition of one pylon pin. - - - - - - - - - - - - - First element (parentAttachmentUID, engineUID - or uID of a pylon structure. - - - - - Second element (parentAttachmentUID, engineUID - or uID of a pylon structure. - - - - - Position of the pylon pin related to the pylon - coordinate system. - - - - - - Blocked DOFs. Refers to the rotated - coordinate system that is defined in 'orientation'. - - - - - - - - UID of the pin. - - - - - - - - - - - - Structural properties of all tibs of the engine pylon - box. - - - - - - - - - - - - - - - - - - - - - - Definition of a rib set. - - - - RibDefinitionType, containing the definition for ribs. - Ribs are defined in sets of one or more ribs. The positions of - the rib, as well as the orientation of the ribs are defined in - 'ribPositioning'. The cross section properties, as e.g. - materials, are defined in 'ribCrossSection'. - - - - - - - - - - - Name of the rib set. - - - - - Description of the rib set. - - - - - - - - - - - - - - - - - pylonRibsPositioningType - - - - Within the ribsPositioning type the position and the - orientation of the ribs of the rib set are defined. - The forward and the rear beginning of the rib set is - defined using relDepthStart and relDepthEnd. The orientation of - the ribs is defined in ribRotaton. The number of ribs of the - current rib set is either defined by ribNumber or by spacing. - - - - - - - - - - - - relDepthStart defines the forward location of - the beginning of the rib set. 0 equals the forward end of the - pylon box, while 1 equals the rear end of the pylon box. - - - - - - relDepthEnd defines the rear end. 0 equals the - forward end of the pylon box, while 1 equals the rear end of the - pylon box. - - - - - Ribs can be rotated in the side view. The - defaults to 90°, which equals an orientation along the pylons - z-axis. The angle is measured around the positive y-direction - of the pylon. - - - - - - The spacing of the ribs defines the distance - between two ribs, measured along the pylons x-axis. First rib - is placed at relDepthStart. - - - - - RibNumber defines the number of ribs in this - ribSet. First rib is at relDepthStart along the pylons x-axis, - last rib is at relDepthEnd. The spacing is constant. - - - - - - - - RibCrossingBehaviour can either be "cross" or - "end". If it is end then ribs will end it they intersect - another rib. It it is cross ribs are placed uncut. - - - - - - - - - - - - - - - - - - - - - Structural properties of pylon shackles (for pylon to - parent attachment), if existing. - - - - - - - - - - - - - - - - - - - - - - - Structural properties of a pylon shackle. - - - - - - - - - - - - - Material properties of the shackle. - - - - - - Link to the structural profile of the shackle. - - - - - - - UID of the shackle. - - - - - - - - - - - - Structural properties of the pylon shells. - - - - - - - - - - - - - - UID of the structural profile. - - - - - - Material settings. - - - - - - UID of the structure. - - - - - - - - - - - - Definition of the load carrying structure of the engine - pylon. - - - - - - - - - - - - - - - - - - - - - - - - - - - - Structural properties of struts (drag struts, upper - links and tangent links), if existing. - - - - - - - - - - - - - - - - - - - - - - - - radiativeForcingType - - - - - - - - - - - - - - - - - - - - - - - - - - - - Rectangle - - - - The width of the profile is always 1, since scaling is performed after referencing it (e.g., in the fuselage). - The resulting profile is defined by the following equation: - - - - - with - c = cornerRadius - and - r = heightToWidthRatio - . - - - Example: Rectangle with - cornerRadius - =0.125 and - heightToWidthRatio - =0.5 - - - - - - - - - - - - - - - - - - - Corner radius - - - - - - - - - - - - - - - - - - Height-to-width ratio - - - - - - - - - - - - - - - - recurringCostType - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Reference values - - - Reference type, containing the reference values of the - aircraft model - - - - - - - - - - Reference area (typically planform area) - - - - - - Reference length (typically Mean Aerodynamic - Chord MAC). In CPACS, only one reference length exists (and is - used, e.g. for all three moment coefficients. Coordinates given - relative to MAC shall always use this length as MAC. - - - - - - Moment reference point (in global coordinate - system). The x-coordinate is typically chosen same as of the - leading edge of the wing in the spanwise section having a - chordlength identical to MAC. Coordinates given as %MAC shall - always use this x-coordinate and length (e.g. 0%MAC = x, 100%MAC - = x + length). The y coordinate is typically 0. The z coordinate - is often chosen either as 0., or as z of fueselage nose or as z - of middle of center fuselage part. - - - - - - - - - - - - - - - - - - - - - - - - - - - Released stores - - - - - - - - - - - - - - - - - - - - - - - - Released store - - - - - - - - - - - - - - - - uID of the released store(s). - - - - - - - Quantity of released stores - - - - - - - - - - - - - - Remaining contributions to aerodynamic coefficients - - - - This node lists the remaining contributions which were not specified so that the sum of the coefficients are equal to the total coefficients. - - - - - - - - - - - - - - - - - - - - Remaining contribution to aerodynamic coefficients - - - - This node lists a remaining contribution which was not specified so that the sum of the coefficients are equal to the total coefficients. - - - - - - - - - - - - Name - - - - - - - Description - - - - - - Type (numerical/unspecified): "numerical", for example, describes rounding errors to clearly - separate them from other effects currently labelled as "unspecified". - The latter usually summarizes physical effects such as viscosity and should be further described via "description". - The approach is currently being tested in practice in order to derive a robust definition of categories in the future. - - - - - - - - - - - - - - - - - - - - - - - - Requirement classification based on the MoSCoW method (must, should, could or wont) - - - - - - - - - - - - - - - - - - - - requirementType - - - - - - - - - - - - - - - - - - - - - - - RibIdentificationType, defining one rib. - - - - - - - - - - - - - UID of the rib definition set. - - - - - - Number of the rib of the rib definition set. - - - - - - - - - - - - - - Definition of the rib rotation - - - The rotation around z describes the rotation around the - wings midplane normal axis. The defaults to 90°. The reference - for the 'zero-angle' of the z-rotation is defined in - ribRotationReference. - - - - - - - - - - RotationReference defines the reference for - the z-rotation it is either sparUID, „LeadingEdge“, - „TrailingEdge“, "globalX", "globalY" or "globalZ". - If it is not defined the rotation reference is - the eta-axis (=leading edge, that is projected on the wings - y-z-plane). A z-rotation angle of 90 degrees means, that the rib - is perpendicular on the ribRotationReference (e.g. spar, leading - edge...). The rib itself is always straight, and the rotation - is defined with respect of the intersection point of the rib - with the ribRotationReference. - - - - - The rotation around z describes the rotation - around the wings midplane normal axis. The defaults to 90°. The - reference for the 'zero-angle' of the z-rotation is defined in - ribRotationReference. - - - - - - - - - - - - - rivetJointAreaAssemblyPositionType - - - RivetJointAreaAssemblyPosition type, containing a rivet - joint area assembly position - - - - - - - - - - - - - - - - - - - - - rivetJointAreasAssemblyType - - - RivetJointAreasAssembly type, containing rivet joint - area assemblies - - - - - - - - - - - - - - - - - - - rivetsType - - - Rivets type, containing rivets - - - - - - - - - - - - - - - - - - - rivetType - - - Rivet type, containing a rivet - - - - - - - - - - Name of the rivet type - - - - - Description of the rivet type - - - - - - Tensile Strength of the rivet type - - - - - - Shear Strength of the rivet type - - - - - - - - - - - - - - - Rotation curve - - - - - The figure below shows an example of a rotation curve. - Together with the corresponding XML code, the definition is explained in more detail. - - - - - - First, the reference system is defined via - referenceSectionUID - , for which in this example the section with - uID="engine_nacelle_fanCowl_section1" - is referenced. - This in turn contains a - transformation - (not shown here), for example a translation by - z=0.4 - and a scaling, where the - x - -direction is stretched by a factor of two. - - - The rotation curve is now described in this reference system. - It is predefined in the profile library and referenced via a its - uID - . - Note that the curve is defined in the range - x=[0,..,1] - in order to be reasonably transformed by the reference system. - - - Next, the blending from the rotated profile of the nacelle segment to the rotation curve is defined. - The corresponding start and end points are given in curve coordinates - zeta - of the corresponding profiles. - Note that the lower part of the segment profile counts from - zeta=[-1,..,0] - and the upper part counts from - zeta=[0,..,1] - . - In between, the blending is linear. - - - - engine_nacelle_fanCowl_section1 - fanCowl_upperSection - -0.6 - -0.5 - -0.2s - -0.1 - - ]]> - - - - Fan cowl rotation curve profile - - 0;0.5;1 - -0.1;-0.2;-0.05 - - - ]]> - - - - - - - - - - UID of the section which serves as reference - - - - - Start zeta [-1,..,1]; relative curve coordante along the rotation curve from which it will be inserted in the nacelle. - - - - - End zeta [-1,..,1]; relative curve coordante along the rotation curve up to which it will be inserted in the nacelle. - - - - - Start zeta for blending [-1..1]; relative curve coordinate along the nacelle profile at which blending from the nacelle profile to the rotation curve will begin. - - - - - End zeta for blending; relative curve coordinate along the nacelle profile at which blending from the rotation curve to the nacelle profile will end. - - - - - UID of the rotation curve profile; the profile should be defined in x=[0..1] to be transformed by the section which is referenced by referenceSectionUID. - - - - - - - - - - - - rotorAirfoilsType - - - RotorAirfoils type, containing rotor airfoil - geometries. See profileGeometryType for further documentation - - - - - - - - - - - - - - - - - - - - rotorBladeAttachmentsType - - - RotorBladeAttachments type, containing all hinges and - blade UIDs attached to the current rotor hub. - - - - - - - - - - - - - - - - - - - rotorBladeAttachmentType - - - RotorBladeAttachment type, defining the elements used - to attach one or more rotor blades to the rotor head. - - - - - - - - - - Name of the blade attachment. - - - - - - Description of the blade attachment. - - - - - - - The azimuthAngles element is used to specify - a list of discrete azimuth angles (in deg) at which instances - of attached blades are to be created. The number of blades will - equal to the number of elements of the vector. E.g. - <azimuthAngles>0;90;180;270</azimuthAngles> for a - four blade rotor with equal equiangularly distributed blades. - The transformation of the respective rotor blade corresponds to - a rotation by azimuthAngle around the z axis of the rotor - coordinate system in mathematically positive sense of rotation. - - - - - - If only the number of blades is specified, - the attached blades will be distributed equiangularly and the - first blade will be attached at azimuth angle 0. (Formula: - azimuthAngle[i] = i*360deg/numberOfBlades, - i=0..numberOfBlades-1) - - - - - - Definition of all hinges used to attach the - rotor blade. - - - - - UID of the rotorBlade which should be attached - to the rotor hub. - - - - - - - - - - - - - - rotorBladesType - - - - RotorBlades type, containing all the rotor blade - gometry definitions of an rotorcraft model. - Rotor blade geometries are defined using the same data - structure as wings (wingType). But in order to be compatible - with the other rotor blade related types (e.g. rotorType, - rotorHubType, rotorHubHingeType) there are some additional - conventions/requirements regarding the definition and - orientation of rotorBlade geometries: - - Rotor blades should be positioned relative to the - global z-axis the way they will be positioned to the rotor - shaft (when blade azimuth=0deg). - The global x-axis should be used as radial axis - (usually the quarter chord line of the rotor blade coincides to - a great extent with the x-axis of the rotor blade coordinate - system). - All sections should be positioned in the positive - x halfspace. - Segments should connect sections with ascending x - coordinates. - Airfoils defined in the rotorAirfoils node should - be used instead airfoils from the wingAirfoils node. - - - - - - - - - - - - - - - - Rotor blade geometries are defined using the - same data structure as wings (wingType). But in order to be - compatible with the other rotor blade related types (e.g. - rotorType, rotorHubType, rotorHubHingeType) there are some - additional conventions/requirements regarding the definition and - orientation of rotorBlade geometries: see remarks. - - - - - - - - - - - - - - rotorcraftAnalysesType, results from several analysis - modules connected to CPACS - - - RotorcraftAnalyses type, containing detailed analysis - data of the rotorcraft - Within this element results from analysis modules are - stored that rely to the overall definition of the rotorcraft. - These include e.g. aerodynamic data or loadCases - For further documentation please refer to the - respective elements. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - rotorcraftGlobalType - - - RotorcraftGlobalType type, containing global data of - the rotorcraft - - - - - - - - - - Number of passenger seats - - - - - Cargo transport capacity [kg] - - - - - - Cruise Mach Number - - - - - Configuration of the rotorcraft: - standard(single main rotor, single tail rotor) / tandem / - coaxial/intermeshing / sideBySide/tiltRotor/tiltWing - - - - - - - - - - - - - - massBreakdownType - - - - - 1. General - - - The - massBreakeDown - is subdivided in - designMasses - , - fuel - , - payload - and - mOME - (operating empty mass). - - - designMass - - The design mass is a description from TLARs and can - be understand as design criteria. - - fuel - and - payload - - The fuel and payload mass are the maximum masses - which can be achieved. Full fuel tanks, all passengers on - board and full cargo holding. - - mOEM - - - The operation empty mass structure is based on the Airbus Mass - Standard brake down [AIRBUS MASS STANDARD 2008]. The - operator’s mass empty (OME) is defined by the sum of the - following component masses: - - operator’s items - manufacturer’s mass empty (MME) - - - - - - - 2. massDescription - - - Each sub component has the following - massDescription - which include a: - - Name - Description - parentUID - Mass value - Mass location - Mass orientation - Mass Inertia. - - - - That - massdescription - can be found at the - designMasses - direct under each item. At the - fuel - , - payload - and - mOME - under massDescription in each item and sub item. - - - - For the clean up the - mOME - there is consisting a script witch is programmed in Matlab but - also as standalone vision available. Setting for that tool can - be done under - toolspesifics/cmu - . - - - - - - - - - - - - - - - - - - - - - - - - - Mass - - - - - - - - - - - - - Manufacturer empty mass description - - - - - - - - - - - - - - - - - Mass - - - - - - - - - - - - - Group mass of hierarchy level 1 - - - - - - - - - - - - - - - Mass - - - - - - - - - - - - - Group mass of hierarchy level 2 - - - - - - - - - - - - - - - Operating empty mass - - - - - - - - - - - - - Operating empty mass description - - - - - - - - - - - - - - - - rotorcraftModelType - - - RotorCraftModel type, containing a complete rotorcraft - model (Geometry and all specific data). The rotorcraftModelType - is basically a copy of the aircraftModelType with the following - additional elements: rotors, rotorBlades, driveSystems. - Furthermore the following elements have been adapted for - rotorcraft: global and analyses (aeroPerformance and - massBreakdown). - - - - - - - - - - Name of rotorcraft model - - - - - Description of rotorcraft model - - - - - - - - - - - - - - - - - - - - - - - - - - Rotorcraft - - - Rotorcraft type, containing all the rotorcraft models. - - Most of the extensions used in the rotorcraft type have - been defined as part of the work in the DLR project RIDE - (Rotorcraft Integrated Design and Evaluation, 2009-2012). - Therefore some of the definitions and conventions are tightly - coupled to the RIDE toolchain and tools. Further generalization - and assimilation of these parts to the definitions for fixed-wing - aircraft is planned for the near future. - - - - - - - - - - - - - - - - - - - Rotor blade elements - - - - RotorBlades type, containing all the rotor blade - gometry definitions of an rotorcraft model. - Rotor blade geometries are defined using the same data - structure as wings (wingType). But in order to be compatible - with the other rotor blade related types (e.g. rotorType, - rotorHubType, rotorHubHingeType) there are some additional - conventions/requirements regarding the definition and - orientation of rotorBlade geometries: - - Rotor blades should be positioned relative to the - global z-axis the way they will be positioned to the rotor - shaft (when blade azimuth=0deg). - The global x-axis should be used as radial axis - (usually the quarter chord line of the rotor blade coincides to - a great extent with the x-axis of the rotor blade coordinate - system). - All sections should be positioned in the positive - x halfspace. - Segments should connect sections with ascending x - coordinates. - Airfoils defined in the rotorAirfoils node should - be used instead airfoils from the wingAirfoils node. - - - - - - - - - - - - - - - - Rotor blade geometries are defined using the - same data structure as wings (wingType). But in order to be - compatible with the other rotor blade related types (e.g. - rotorType, rotorHubType, rotorHubHingeType) there are some - additional conventions/requirements regarding the definition and - orientation of rotorBlade geometries: see remarks. - - - - - - - - - - - - - - Rotor blade - - - - - - - - - - Name of the wing. - - - - - Description of the wing. - - - - - - - - - - - - - - - - - - - Rotor - - - - - - - - - - - - - - - - - - - Rotor type, containing a rotor (main rotor, tail rotor, - fenestron, propeller,...) of an rotorcraft model. - - - - Rotor type, containing a rotor (e.g. main rotor, tail - rotor, fenestron, propeller,...) definition of a rotorcraft - model. - The position and attitude of the rotor is defined - using the transformation element. The following image shows the - CPACS conventions for the orientation of rotors and rotor axis - systems: - - - - - The origin coincides with the center of rotation. - - The z-axis corresponds to the axis of rotation - and thus coincides with the rotor shaft centerline. It Points - in the main thrust direction of the rotor (usually upwards for - a main rotor, forwards for a propeller). - The x-axis points from nose to tail (usually - rearwards for main and tail rotors, upwards for a propeller). - - The y-axis completes the right-handed orthogonal - coordinate system. - - Rotor hub attributes, hinges and references to - attached rotor blades are defined in the rotorHub element. - - - Note that rotor blade geometries are only referenced and not - defined in the child nodes of the rotor element. Refer to the - documentation of rotorBladesType ( - Empty#T/rotorBladesType - ) and wingType ( - Empty#T/wingType - ) for information on the definition of rotor blade geometries. - - The following figure shows the transformations to be - applied to rotorBlade geometries to visualize them in the rotor - frames for a given state (each rotor: rotorAzimuth given, each - hinge: hingeDeflection given): - - - - - - - - - - - - - - Name of the rotor. - - - - - Description of the rotor. - - - - - Nominal value of the angular rotation speed in - rotations per minute (rpm). - - - - - The rotorHub element contains the definition - of the rotor hub type and number and azimuth angles of the - attached blades and their hinges. The rotor hub position and - attitude coincides with the rotor axis system's origin and z - axis. - - - - - - - - - - - - - - - Rotor elements - - - - - - - - - - - - - - - - - - - - rotorHubHingesType - - - RotorHubHinges type, defining hinges used to attach a - rotor blade to the rotor head. - - - - - - - - - - Definition of a flap, lead-lag or pitch hinge. - - - - - - - - - - - - - - rotorHubHinge type, containing a rotor hub hinge - (flap/leadLag/pitch). - - - - RotorHubHinge type, containing a rotor hub hinge - (flap/leadLag/pitch) of a rotorcraft model. - - - - - - - - - - - Name of the hinge. - - - - - Description of the hinge. - - - - - - Hinge type. Possible values: "flap", "pitch" - "leadLag". This is used to define the rotation axis of the hinge - (flap = y-axis in blade cs, pitch = x-axis in blade cs, lead-lag - = z-axis in blade cs). - - - - - - - - - - - - The angle (in deg) at which the hinge is in - neutral position. This element is normally used to define - precone or prelag angles of the attached blade. Defaults to 0. - - - - - - Static stiffness of the hinge in (N/m) for - linear hinges and (N.m/deg) for angular hinges. Default value: - +inf (statically rigid hinge) - - - - - Dynamic stiffness of the hinge in (N/m) for - linear hinges and (N.m/deg) for angular hinges. Default value: - +inf (statically rigid hinge) - - - - - Damping of the hinge in (N/(m/s)) for linear - hinges and (N.m/(deg/s)) for angular hinges. Default value: +inf - - - - - - - - - - - - - - - rotorHubType - - - RotorHub type, containing definitions for the rotor hub - and attached hinges and blades. - - - - - - - - - - Name of the rotor hub. - - - - - Description of the rotor hub. - - - - - - Rotor head type. Possible values: "semiRigid", - "rigid", "articulated", "hingeless" - - - - - - - - - - - - - Rotor blade attachments are used to define how - many rotor blades are attached at which azimuth positions of the - rotor hub and the used hinges. - - - - - - - - - - - - - - rotorsType - - - Rotors type, containing all the rotors (mainRotors, - tailRotors, fenestrons, propellers, ...) of an rotorcraft model. - - - - - - - - - - - - - - - - - - - - Rotor type, containing a rotor (main rotor, tail rotor, - fenestron, propeller,...) of an rotorcraft model. - - - - Rotor type, containing a rotor (e.g. main rotor, tail - rotor, fenestron, propeller,...) definition of a rotorcraft - model. - The position and attitude of the rotor is defined - using the transformation element. The following image shows the - CPACS conventions for the orientation of rotors and rotor axis - systems: - - - - - The origin coincides with the center of rotation. - - The z-axis corresponds to the axis of rotation - and thus coincides with the rotor shaft centerline. It Points - in the main thrust direction of the rotor (usually upwards for - a main rotor, forwards for a propeller). - The x-axis points from nose to tail (usually - rearwards for main and tail rotors, upwards for a propeller). - - The y-axis completes the right-handed orthogonal - coordinate system. - - Rotor hub attributes, hinges and references to - attached rotor blades are defined in the rotorHub element. - - - Note that rotor blade geometries are only referenced and not - defined in the child nodes of the rotor element. Refer to the - documentation of rotorBladesType ( - Empty#T/rotorBladesType - ) and wingType ( - Empty#T/wingType - ) for information on the definition of rotor blade geometries. - - The following figure shows the transformations to be - applied to rotorBlade geometries to visualize them in the rotor - frames for a given state (each rotor: rotorAzimuth given, each - hinge: hingeDeflection given): - - - - - - - - - - - - - - Name of the rotor. - - - - - Description of the rotor. - - - - - UID of the part to which the rotor is mounted - (if any). The parent of the rotor can e.g. be the fuselage. In - each rotorcraft model, there is exactly one part without a - parent part (The root of the connection hierarchy). - - - - - - Rotor type. Possible values: "mainRotor" - (default), "tailRotor", "fenestron" or "propeller".. - - - - - - - - - - - - - - Nominal value of the angular rotation speed in - rotations per minute (rpm). - - - - - Transformation (scaling, rotation, - translation). This element is used to define the position and - attitude of the rotor relative to the global or the parent - component's axis system. Note that an anisotropical scaling - transformation should not be applied to the rotor. - - - - - - The rotorHub element contains the definition - of the rotor hub type and number and azimuth angles of the - attached blades and their hinges. The rotor hub position and - attitude coincides with the rotor axis system's origin and z - axis. - - - - - - - - - - - - - - - runwayILSType - - - RunwayILS type, containing ILS data of a runway - - - - - - - - - - - Position of the localizer antenna - - - - - - - Position of the glide slope antenna - - - - - - Angle of the glide path - - - - - - - - - - - - - - Runway start position - - - - - Description of the vehicle on the runway relative to the runway threshold. - - - - - - - - - - - - - - X-position in cartesian coordinates in the runway coordinate system - - - - - - - Y-position in cartesian coordinates in the runway coordinate system - - - - - - - Z-position in cartesian coordinates in the runway coordinate system - - - - - - - - - Lengthwise distance along the runway centerline from the runway threshold - - - - - - - Lateral offset from the runway centerline. Positive values on the starboard side. - - - - - - - - - - - - - - - runwaysType - - - Runways type, containing data of the airport's runways - - - - - - - - - - - - - - - - - - - - runwayType - - - Runway type, containing data of a runway - - - - - - - - - - Name of runway - - - - - Description of runway - - - - - Position in degrees north - - - - - Position in degrees east - - - - - Threshold elevation - - - - - Runway heading - - - - - Takeoff run available - - - - - Landing distance available - - - - - Conditions of the runway - - - - - - - - - - - - - - - Seat elements - - - Seat element collection type - - - - - - - - - - Seat element for use in the decks - - - - - - - - - - - - - Seat element - - - Seat element type, containing the base elements of the cabin - - - - - - - - - - Description - - - - - - - Number of seats - - - - - - - - - - - - - - Seat modules - - - Seat module instance collection type. - - - - - - - - - - Seat module - - - - - - - - - - - - - shaftLinkedComponentsType - - - ShaftLinkedComponents type, containing UIDs of engines, - transmissions and rotors linked by a shaft. - - - - - - - - - - - UID of a linked engine. - - - - - UID of a linked transmission shaft input. - - - - - - UID of a linked transmission shaft output. - - - - - - UID of a linked rotor. - - - - - - - - - - - - - - shaftsType - - - Shafts type, containing all the shafts of a drive - system. - - - - - - - - - - - - - - - - - - - shaftType - - - Shaft type defining a shaft used as a link between - drive system components. - - - - - - - - - - - - - - - - - - - - - - sheet3DType - - - - - - - - - - - - - - - - - - - - - - - - - sheetBasedStrcuturalElementsType - - - sheetBasedStrcuturalElementsType, containing sheet - based structural element definitions - - - - - - - - - - - - - - - - - - - sheetBasedStructuralElementType - - - sheetBasedStructuralElementType type, sheet definition - for use in fuselage/structure - - - - - - - - - - Material definition of the skin segment - (Material, thickness, (lay-up)) - - - - - - - - - - - - - - sheetList3DType - - - - - - - - - - - - - - - - - - - - - - List of sheets, connecting 2-dimensional profile - points. - - - SheetList type, containing a list of sheets. Each sheet - combines two points to one sheet. - - - - - - - - - - - - - - - - - - - sheetPointsType - - - - - - - - - - - - - - - - - - - - - - sheetType - - - Sheet type, containing connection data of a sheet - - - - - - - - - - - Name of sheet within the profile definition - - - - - - Description of sheet within the profile - definition - - - - - Point from which the sheet definition starts - start - - - - - Continuity definition for profile geometry - generation. 0= C0 (allows sharp edges, default), 1= C1 (defines - tangential continuity), 2= C2 (defines curvature continuity) - 2=all - - - - - - - - - - - - - - Definition of an orientation vector at P1 - - - - - - Point at which the sheet definition ends - - - - - - Continuity definition for profile geometry - generation. 0= C0 (allows sharp edges, default), 1= C1 (defines - tangential continuity), 2= C2 (defines curvature continuity) - 2=all - - - - - - - - - - - - - - Definition of an orientation vector at P2 - - - - - - - - - - - - Side strut(s) (Assumption: one end of the strut will connect to the main strut and the other end will be given as endPoint) - - - - - - - - - - - - Sidewall panel elements - - - Sidewall panel element collection type - - - - - - - - - - Sidewall panel element for use in the decks - - - - - - - - - - - - - Sidewall panels - - - Sidewall panel instance collection type. - - - - - - - - - - Sidewall panel - - - - - - - - - - - - - - singleGenericMassType - - - - - - - - - - - - - - - - - - - - - - Skid landing gears - - - List of skid gears - - - - - - - - - - - - - - - - - - - fuselageSkinSegmentType - - - FuselageSkinSegment type, containing material on skin - over circumference - - - - - - - - - - - - - - - - - - - fuselagePanelType - - - FuselagePanel type, panel of the fuselage between - stringers/ frames (new in V1.5) - - - - - - - - - - UID of sheetBasedStructuralElement used for - the panel - - - - - UID of frame at start of the skin segment - - - - - - UID of frame at end of the skin segment - - - - - - UID of stringer at start of the skin segment - - - - - - UID of stringer at end of the skin segment - - - - - - - - - - - - - - - skinType - - - Containing data defining the skin - - - - - - - - - - Default UID of sheetBasedStructuralElement - used for the fuselage skin not covered by individual panels - - - - - - - - - - - - - - - Source / Target - - - - - - - - - - - UID of a component defined under aircraft(rotorcraft)/model - - - - - - UID of a sub-component - - - - - - - External element (ambient | passengers), which is not explicitly defined in CPACS. - External elements indicate that this is an element relevant to modeling the system, but is not itself contained in the system. - - - - - - - - - - - - - - - Source / target system according to ATA chapter - - - - - - UID of another systemArchitecture - - - - - - - - - - - - - - SparCells of current spar. - - - sparCells are an optional Element. They are defined via - the etaCoordinates and define a region of special cross section - and material properties. - - - - - - - - - - - - - - - - - - - Spar cell of the spar. - - - - Within spar cells a special area of the spar is - defined where different cross section and material properties - shall be defined. - The area of the spar is defined by using the - parameters 'fromEta' and 'toEta'. The definition of the caps, - webs and rotation is equivalent to the cross section definition - of the complete spar. - - - - - - - - - - - Beginning (= inner border) of the spar cell. - - - - - - Ending (= outer border) of the spar cell. - - - - - - Upper Cap - - - - - - Lower Cap - - - - - - Web 1 - - - - - - Web 2 - - - - - - The angle between the wing middle plane and - web 1 [deg]. Default is 90 degrees. Positive rotation is around the - spar axis heading along with the positive eta-axis. - - - - - - - - - - - - - - - Definition of the spar cross section. - - - - Spar type, containing the cross section definition of - a spar. The spar middle point is defined by the intersection of - the wing middle plane and web1. This equals the coordinate - defined within the sparPosition. - Please find below a picture where all spar cross - section parameters as well as the orientation references for - the material definition can be found: - - - - - - - - - - - - - - - - - - - The angle between the wing middle plane and - web1. Default is 90 degrees. Positive rotation is around the - intersection axis of the spar and the wing middle plane. The - positive heading of this axis is inline with the positive - heading of the componentSegment eta-axis. - - - - - - - - - - - - - Spar definition points on the wing. - - - - sparPositionType, a sparPostion defines a location - within the componentSegment where a spar in mounted. Eta and xsi - are relative to the componentSegment. - Please find below a picture for an example definition - of 3 spars in one wing, by using spar position points and spar - segments: - - - - - - - - - - - - - - - - - - - - - - - Spar position on the wing - - - - sparPositionType, a sparPostion defines a location - within the componentSegment where a spar in mounted. Eta and xsi - are relative to the componentSegment. - Please find below a picture for an example definition - of 3 spars in one wing, by using spar position points and spar - segments: - - - - As an alternative to the relative eta coordinate it is - possible to specify an elementUID so that the spar position is - relative to the outer geometry, e.g. kink, of the wing. - - - - - - - - - - - - Defines a spar position on an existing rib using a relative xsi coordinate - to determine the chord wise position on that rib - - - - - Defines a spar position using relative eta/xsi coordinates - - - - - Defines a spar position via a point on a curve - - - - - - - - - - - - - - sparPositionUIDs of the spar. - - - - sparPositionType, a sparPostion defines a location - within the componentSegment where a spar in mounted. Those - positions are combined to spars by using a list of spar position - uIDs. The order of the sparPositionUIDs must be the same as the - order of the points on the real spar (from root to tip or from - tip to root). - Please note: orientation of a spar must be always - outbound or always inbound. A zigzag spar orientation where - e.g. the spar starts at the root, goes to the tip and goes back - to another point at the root is not allowed. - Please find below a picture for an example definition - of 3 spars in one wing, by using spar position points and spar - segments: - - - - - - - - - - - - - - List of spar position uIDs. - - - - - - - - - - - - - - Spar segments of the wing. - - - sparSegmentsType, containing multiple sparSegment - (=spars) of the wing. - - - - - - - - - - - - - - - - - - - SparSegments (=spars) of the wing. - - - SparSegmentType, each spar is defined by multiple - sparPositions that are referenced via their uID. The spar cross - section is defined in 'sparCrossSection'. - - - - - - - - - - Name of the spar segment (=spar). - - - - - - Description of the spar segment (spar). - - - - - - - - - - - - - - - - - Species - - - - - - - - - - Share - - - - - - - - - - - - - - - - - - - - Species type - - - - - - - - - - - - - - - - - - List of segment uIDs to which the configuration is to be applied - - - - - - - - - - - - - - - - - - - - - - - - Specification of a segment uID and index of the parameter lapses - - - - - - - - - - - - - - - - UID of the segment for which the specific configuration holds. - - - - - - - Vector with semicolon separated indices of the parts of the respective segment within the mission definition for which the specific configuration setting holds. Example: scheduling configurations for a climb or descent segment (different settings of moveables and gears) on altitudes/velocities - - - - - - - - - - - - - - Specific configuration uIDs - - - - - - - - - - - - - - - - - - - - - - - - Connection between segments, pointPerformances and a configurationUID - - - - - - - - - - - - - - - - Configuration uID - - - - - - - - List of pointPerformanceUIDs - - - - - - - - - - - - - - Specific heat map, containing the specific heat capacity of a material at different temperatures. - - - The specific heat of a material can vary with the temperature. The vectors specificHeat and temperature - must have the same size to be valid. The data should be linearly interpolated. - - - - - - - - - - - Temperature in [K] - - - - - Specific heat capacity of the material in [J/(kg*K)] - - - - - - - - - - - - - specificPerformanceMapsType - - - Collection of all assignments of specific performance maps to selected mission segments - - - - - - - - - - - - - - - - - - - Specific performance map - - - - - Applying a specific performance map to selected mission segments. In addition to the obligatory - defaultPerformanceMapUID - at least a - segmentUID - or - pointPerformanceUID - must be given. - - - - - - - - - - - - UID of performance map to be used for mission segments - - - - - - - List of all mission segment UIDs to which the performance map is to be applied - - - - - List of point performance UIDs to which the performance map is to be applied - - - - - - List of point performance UIDs to which the performance map is to be applied - - - - - - - - - - - - - - Speed designators - - - - Provides an enumerated list of V-speeds as defined by regulations. - - - - - - - - - - - Design maneuvering speed - - - - - - - Design speed for maximum gust intensity - - - - - - - Design cruise speed, used to show compliance with gust intensity loading - - - - - - - Design diving speed, the highest speed planned to be achieved in testing - - - - - - - Designed flap speed - - - - - - - Stall speed or minimum steady flight speed for which the aircraft is still controllable - - - - - - - Stall speed or minimum flight speed in landing configuration - - - - - - - Stall speed or minimum steady flight speed for which the aircraft is still controllable in a specific configuration - - - - - - - Minimum control speed - - - - - - - Never exceed speed - - - - - - - Maximum operating limit speed - - - - - - - - - - - - - Sphere - - - A sphere is defined with a default volume of 1m3. - - - - - - - - - - Radius (default=cubicRoot(3/(4pi))=0.62035) [m] - - - - - - - - - - - - - Definition of the wings spoilers. - - - Definition of the wings spoilers. - - - - - - - - - - - - - - - - - - - Spoilers of the wing. - - - A spoiler is defined via its outerShape relative to the - componentSegment. The WingCutOut defines the area of the upper - skin that is removed by the spoiler. Structure is similar to the - wing structure. The mechanical links between the spoiler and the - parent are defined in tracks. The deflection path is described - in path. Additional actuators, that are not included into a - track, can be defined in actuators. - - - - - - - - - - Name of the spoiler. - - - - - Description of the spoiler. - - - - - - UID of the parent of the spoiler. The parent - is the componentSegment, where the spoiler is attached. - - - - - - - - - - - - - - - - - - - - - Standard profile - - - - - - - - - - - - - - - - - - - - - - - State parameters list - - - Contains a list of all state parameters. - - - - - - - - - - - - - - - - - - - - State parameter definition - - - Contains the values of a parameter and its uid as reference. - - - - - - - - - - - - - - - - - - - - - - - - Static power breakdowns - - - - - - - - - - - - - - - - - - - Static power breakdown case - - - - - - - - - - Name - - - - - Description - - - - - - - - - - - - - - - - stiffnessType - - - - - - - - - - - - - - - - - - - - - - - - - - - Stored chemical energies - - - - - - - - - - - - - - - - - - - Stored chemical energy - - - - - - - - - - - - - Fill factor - - - - - - - - - - - - Fill factor reference (optimalVolume | usableVolume | realVolume) - - - - - - - - - - - - - - - - - - - - - - - Stored electrical energy - - - - - - - - - - - Charge level - - - - - - - - - - - - - - - - - - - - - Stored electric energies - - - - - - - - - - - - - - - - - - - stringArrayBaseType - - - Base type for string array nodes (including maptype - array attribute) - - DEPRECATED: As of CPACCS version 3.3, the - mapType - attribute is set to optional to ensure the compatibility of older data records. However, since the type is uniquely defined via the XSD, the attribute is superfluous and will therefore be completely omitted in future versions. - - - - - - - - - - - - - - - - - - stringBaseType - - - Base type for string nodes (including external data - attributes) - - - - - - - - - - - - - - - - - - - stringerFramePositionType - - - - Description of individual stringer / frame positions - - - - - - - - - - - - - - UID of profile based structural element - - - - - - - x position in absolute value - - - - - - UID reference to a fuselageSectionElement - - - - - - - y coordinate of reference system - - - - - - z coordinate of reference system - - - - - - angle definition to calculate intersection - with loft - - - - - - Continuity definition for profile extrusion: - 0= C0 (allows sharp edges, default), 2= C2 (defines curvature - continuity) - - - - - - - - - - - - - Definition of interpolation between different - profiles: 0= no interpolation 1= interpolation of structural - profile - - - - - - - - - - - - - - - - - - - - - - - framePositionUIDs of the frame - - - - - A framePostion defines a location where a frame in mounted. - - - - - - - - - - - framePositionUID of the frame, where the landing gear - is attached to. - - - - - - - - - - - - - stringersAssemblyType - - - StringersAssembly type, containing an assembly of - stringers (new V1.5) - - - - - - - - - - - - - - - - - - - arbitraryStringerType - - - ArbitraryStringer type, containing stringer definition - (CPACS V1.5+) - - - - - - - - - - - - - - - - - - - - stringUIDBaseType - - - This is the base type that links to other components. It should always contain a UID. - This node has an additional attribute isLink that will be used if a stringBaseType refers to a uID. TIXI can then - perform automatic validation for the existence of the referenced uID. - Furthermore this node contains an additional attribute symmetry. The symmetry attribute may take three values: symm, def, full - def: The element refers to the geometric component that has a symmetry attribute and refers only to the defined side of the geometric component. - symm: The element refers to the geometric component that has a symmetry attribute and refers only to the symmetric side of the geometric component. (Similar to the previous _symm solution) - full: The element refers to the geometric component that has a symmetry attribute and refers to the complete component. (This is the default behaviour) - - - - - - - - - - DEPRECATED - : The - isLink - attribute is set to optional to ensure the compatibility of older data records. However, since the linking character is explicitly defined by the - stringUIDBaseType - , the attribute is superfluous and will therefore be completely omitted in future versions. - - - - - - - - - - - - - - - - - - - - - - stringVectorBaseType - - - - Base type for string vector nodes - The vector base type can include optional uncertainty - information. The description of uncertainties is placed in - additional attributes. First, it is described by an attribute that - describes the type of uncertainty function called functionName. - The functionName attribute includes the tag name of the - distribution function which is listened in the table shown below. - Each uncertainty function is further describes by a set of - parameters that are described in the table below. - If the uncertainty values change for the elements of - the vector than the attribute may be written as a list of values - separated by semicolons - - DEPRECATED: As of - CPACS - version 3.3, the - mapType - attribute is set to optional to ensure the compatibility of older data sets. - However, since the type is uniquely defined via the XSD, the attribute is superfluous - and will therefore be completely omitted in the next major release (Note: requires - TiXI >= 3.3). Please contact the - CPACS - team - if for any reason you see a long-term need for the - mapType - attribute. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Structural elements - - - structuralElements Type, containing the different structural - elements - - - - - - - - - - - - - - - - - Seat elements (Deprecation warning: This element will soon be removed from the official CPACS. Use the new seat modules located at cpacs/vehicles/deckElements!) - - - - - - - - - - - - - - - Structural mount - - - - - - - - - - - - - - If this value is set to true then only the end points of the intersection shall be included as nodes in the model. - - - - - - The UID for the first connection UID may include for wings: skin, sparUID, ribDefinitionUID, ribNumber, stringerUID, stingerNumber, and for fuselages: skinSegmentUID, frameUID, stringerUID, crossBeamUID, crossBeamStrutUID, longFloorBeamUID. - - - - - - Optional counter to specify numbered items, e.g. ribs in a ribSet. - - - - - - The UID for the second connection UID may include for wings: skin, sparUID, ribDefinitionUID, ribNumber, stringerUID, stingerNumber, and for fuselages: skinSegmentUID, frameUID, stringerUID, crossBeamUID, crossBeamStrutUID, longFloorBeamUID. - - - - - - Optional counter to specify numbered items, e.g. ribs in a ribSet. - - - - - - - - - - - - - - - structuralProfile3DType - - - - - - - - - - - - - - - - - - - - - - - - - - Definition cross sections of structural profiles. - - - - Structuralprofiles type, containing cross section - information of structural profiles. - - - - - - - - - - - - - - - - - - - - 2-dimensional cross sections of structural profiles. - - - - - StructureProfile type, containing data of a structure - profile cross sections. The cross section profile is defined by - several points (->pointList) in the x-y-space. Two points are - combined to one sheet (->sheetList) by using the pointUIDs. - - This profile is defined by several points in the - x-y-space. Always two points are combined to one sheet. The - properties of each sheet are defined in the 'sheetProperties' - section by referencing on the sheetUID and the material - properties. The orthotropy direction of composite materials equals - the x-sheet axis. The orthotropy direction angle equals a positive - rotation around the z-sheet axis as indicated in the picture below - (part 3.), where a wing stringer is defined as an example: - - - - - - - - - - - - - - - Name of the structure profile. - - - - - - Description of the structure profile. - - - - - - List of structural profile points, only x and - y. - - - - - - - - - - - - - - - - Structural wall reinforcement definition specifying physical properties of a fuselage wall segment. - - - - - - - - - - - - - - Reference to a sheet element definition specifying the physical properties of the wall's shell. - - - - - Reinforcements running along the position polygon of the wall positions. - - - - - Reinforcements running in lateral/radial direction in the wall segment plane. - - - - - Reinforcement at inner side of wall. This is either, depending on the extrusion direction flag, the edge of the wall that connects the positions ("positiveDirection") or the edge of the wall where the wall intersects with the fuselage skin in the opposite direction of the extrusion direction. - - - - - - Reinforcement at outer side of wall. The outer side of the wall is defined as the edge of the wall at the intersection of the wall with the fuselage skin running along the main direction of the wall. - - - - - - - Lateral caps are the reinforcements of - the wall at the edges lateral to the - main direction of the wall. These caps - can be either defined at start, end, - start and end or at all wall positions - according to the placement flag. - - - - - - - - - - - - - - - Strut assembly - - - Geometric description, spatial placement and specification of material parameters - - - - - - - - - - Strut properties - - - - - The starting point of the support strut must connect to the main strut. This element specifies the relative position on the main strut (0 -> top end, 1 -> bottom end). - - - - - - - - - - - - End position in absolute coordinates. Coordinates are relative to parent if it has a parentUID reference (otherwise global). - - - - - End position in eta/xsi/relHeight coordinates - - - - - End position as a relative position on another strut of this landing gear - - - - - - Attachment to an aircraft wing or fuselage component - - - - - Reference to an actuator uID - - - - - - - - - - - - - - - Strut properties - - - - - Geometric description and material properties - of a strut - - - - - - - - - - - - - (Outer) radius of the strut - - - - - - Material of the strut - - - - - Inner radius of the strut - - - - - - - - Reference to structural element for a more - detailed cross section definition - - - - - - - - - - - - - - - Geometric description and material properties of a strut - - - - - - - - - - Length of the strut - - - - - - - - - - - - - - Design study parameters and results - - - - Contains optimization data such as definitions of design parameters and design studies. - - - - - - - - - - - - - - - - - - - - - - - - - subFleetsType - - - Contains a list of different sub fleets - - - - - - - - - - - - - - - - - - - subFleetType - - - Each fleet can be divided into sub fleet groups - - - - - - - - - - Name of fleet - - - - - Description of the fleet - - - - - A ; separated list of all tailsign strings - - - - - - - - - - - - - - subLoadType - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Superellipse - - - - A profile based on superellipses is composed of an upper and a lower semi-ellipse, which may differ from each other in their parameterization. The total width and height of the profile is always 1, since scaling is performed after referencing (e.g., in the fuselage). - - This - lowerHeightFraction - describes the portion of the lower semi-ellipse on the total height. - - The resulting profile is defined by the following set of equations: - - - - - - - with - - - - The following examples indicate the various possibilities of parametric profiles: - - Example 1 - : ( - mUpper,nUpper,mLower,nLower, lowerHeightFraction - ) = (0.5; 2; 5; 3; 0.25) - - - - - - Example 2 - : ( - mUpper,nUpper,mLower,nLower, lowerHeightFraction - ) = (2; 2; 2; 2; 0.5) = a circle - - - - - - Example 3 - : ( - mUpper,nUpper,mLower,nLower, lowerHeightFraction - ) = (1; 1; 1; 1; 0.5) = a square / diamond - - - - - - Note - : For exponents that are infinitely large, the superellipse converges to a rectangle. However, the value - Inf - is not a valid entry at this point. Use the - square - element instead. - - - - - - - - - - - - Exponent m for upper semi-ellipse - - - - - Exponent n for upper semi-ellipse - - - - - Exponent m for lower semi-ellipse - - - - - Exponent n for lower semi-ellipse - - - - - - Fraction of height of the lower semi-ellipse relative to the total height - - - - - - - - - - - - - - - - - - - - Main landing gear support beam - - - - Definition of the main landing gear support beam, if a - support beam is used for the attachment. The definition includes - cross section properties as well as the position of the support - beam. - - - - - - - - - - - - - - - - - - - - Symmetry (see CPACS root node documentation for details) - - - - - - - - Symmetry inheritance from parent element disabled - - - - - Symmetry inherited from parent element (default behavior, i.e. also applies if attribute not set) - - - - - Symmetry w.r.t. the x-y plane of the CPACS coordinate system - - - - - Symmetry w.r.t. the x-z plane of the CPACS coordinate system - - - - - Symmetry w.r.t. the y-z plane of the CPACS coordinate system - - - - - - - - - - - System element - - - - - - - - - - Name - - - - - Description - - - - - - - Density - - - - - Mass - - - - - - - - - - - - - - - System architectures - - - - - - - - - - - - - - - - - - - System architecture - - - - - - - - - - Name - - - - - Description - - - - - ATA Chapter | generic - - - - - - - - - - - - - - - - Connections - - - - - - - - - - - - - - - - - - - Connection - - - - - - - - - - Name - - - - - Description - - - - - Type of the connection. - - - - - - - - - - - - - - - - - - - - - - - - - - - - Control devices - - - - - - - - - - Control function indicating the activation state - - - - - - - - - - - - - - System elements - - - - - - - - - - - - - - - - - - - - - - - - - - Control parameter definition for System or Connection state - - - - - - - - - - Control parameter indicating active state - - - - - Control parameter indicating inactive state - - - - - - - - - - - - - Systems - - - - Systems type, containing the aircraft's control system - data - Please see the attached picture for further - documentation - - - - - - - - - - - - - - Node for geometrical layout of system components - based on simple geometric shapes - - - - - - Cockpit controls, e.g. stickRoll, pedals - - - - - - Different commandCases that are commanded, - e.g. roll, accelerate - - - - - Control Distributors, deliver inputs to the - control actuators. E.g. different angles of different ailerons. - - - - - - Control laws, for regulated actuation - - - - - - - - - - - - - - - - - - tailplaneAttachmentAreaType - - - tailplaneAttachmentArea type, containing dat on - fuselage - structure to attach tailplaine - - - - - - - - - - Definition of tailplane attachment area - (Standard - Configuration) - - - - - type of tailplane attachment: Currently - restricted to - 'Type1' and 'Type2' (see documentation) - - - - - - - - - - - - - - Definitions of VTP interface - - - - - - Definitions of VTP interface - - - - - - - - - - - - - - - takeoffPerformanceParametersType - - - - - - - - - - - - - Take-off distance at liftoff speed VLOF. - - - - - - Take-off distance at safety speed V2. - - - - - - Optimal speed Velev at point of initiating - take-off rotation by elevator deflection for a minimum take-off - distance. - - - - - Optimal rotation speed VR for a mini-mum - take-off distance - - - - - Liftoff speed VLOF. - - - - - Safety speed V2. - - - - - Take-off decision speed V1 - - - - - Minimum control speed ground VMCG. - - - - - - Flight path angle being achieved at V2 with - one engine failure in 400 ft height above ground. This is the - result of a post trim calculation using the deter-mined V2. If - the trim calculation fails the entry is set to -90. - - - - - - - - - - - - - - Structural properties of the tangent links, if - existing. The tangent links do connect the engine pylon with the - engine to carry the thrust forces. - - - - - - - - - - - - - - - - - - - - - - simpleConnectionsType - - - SimpleConnections type, containing simple connections - - - - - - - - - - - - - - - - - - - - simpleConnectionType - - - SimpleConnection type, containing a simple connection - - - - - - - - - - - Can be each structural member (skinSegment, - stringer, frame, paxCrossBeam, cargoCrossBeam, - paxCrossBeamStrut, cargoCrossBeamStrut, long. floor beams, - floorPanel, seatModule) - - - - - Can be each structural member (skinSegment, - stringer, frame, paxCrossBeam, cargoCrossBeam, - paxCrossBeamStrut, cargoCrossBeamStrut, long. floor beams, - floorPanel, seatModule) - - - - - - - - - - - - - - timeBaseType - - - Base type for time nodes (including external data attributes) - This time type is based on the xsd:time definition. - "To specify a time zone, you can either enter a time in UTC time by adding a "Z" behind the time - like this: 09:30:10Z - or you can specify an offset from the UTC time by adding a positive or negative time behind the time - like this: - 09:30:10-06:00 - or - 09:30:10+06:00" (description taken from http://www.w3schools.com/xml/schema_dtypes_date.asp) - - - - - - - - - - - - - - - - - - - timeConstraintBaseType - - - - Base type for time nodes including a relational operator attribute indicating valid constraint region - The timeConstraintBaseType extends the timeBaseType and thus inherits all its attributes. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Toolspecific data - - - - This type contains a list of tools each specifying some basic tool information as well as the actual toolspecific part. - - The toolspecific elements must be defined in a separate namespace which can be specified and linked with the corresponding XSD file - in the CPACS header: - <cpacs xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" - xsi:noNamespaceSchemaLocation="pathToSchemaFile/cpacs_schema.xsd" - xsi:schemaLocation="http://www.cpacs.de/myTool pathToToolspecificSchemaFile/toolspecific_myTool.xsd"> - A simple example could look like this: - <toolspecific> - <tool> - <name>myToolName</name> - <version>1.2.3</version> - <myTool xmlns="http://www.cpacs.de/myTool" schemaVersion="1.0"> - <parentElement> - <childElement1>stringValue</childElement1> - <childElement2>1.0</childElement2> - </parentElement> - </myTool> - </tool> -</toolspecific> - - - - - - - - - - - - - - - - - - - - Tool identification - - - - Tool information as described in the toolspecificType. - - - - - - - - - - - - Name of the tool - - - - - - - Version of the tool - - - - - - - Wildcard for the root element of a toolspecific namespace - - - - - - - - - - - - - - topologyEntriesType - - - - - - - - - - - - - - - - - - - - - - topologyEntryType - - - A topology entry is used to combine the dynamic aircraft - models of several components, e.g. wing and fuselage. By default - these will be stiff. If desired stiffness and rotation with - respect to the CPACS coordinate system may be specified. - - - - - - - - - - - - - - - - - - - - - - - Torispherical dome - - - - - - - - - - R1: dish radius - - - - - R2: knuckle radius - - - - - - - - - - - - - totalOperatingCostType - - - - - - - - - - - - - - - - - - - - - - - - trackActuatorType - - - - - - - - - - - - - Reference to the uID of the actuator of the - track. - - - - - Definition of the material properties of the - actuator to track attachment. - - - - - - - - - - - - - - Joint coordinates - - - - Definition of a joint coordinates. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Specification of joint coordinates. - - - - Specification of joint coordinates. - - - - - - - - - - - - - - - - - - - - Set of joint coordinates - - - - Definition of a set of joint coordinates. - - - - - - - - - - - Value of the command parameter of a control distributor. If not given explicitly in the control distributor, linear interpolation between the neighboring points is required. - - - - - - - - - - - - - - - - - - - - - - - - wingSparsType - - - Spars type, a spar is defined by sparSegments that - stretch between multiple sparPositions - - - - - - - - - - - - - - - - - - - - - - - - - - - - Definition of the struts of a control surface track. - - - - Definition of the struts of a control surface track. - - - - - - - - - - - - - - - - - - - - Definition of a strut of a control surface track. - - - - Definition of a strut of a control surface track. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Definition of the wings trailing edge devices. - - - - Definition of the wings trailing edge devices. - - - - - - - - - - - - - - - - - - - - Trailing edge device of the wing. - - - A trailingEdgeDevice (TED) is defined via its - outerShape relative to the componentSegment. The WingCutOut - defines the area of the skin that is removed by the TED. - Structure is similar to the wing structure. The mechanical links - between the TED and the parent are defined in tracks. The - deflection path is described in path. Additional actuators, that - are not included into a track, can be defined in actuators. - - Leading and trailing edge are defined by the outer - shape of the wing segments, i.e. the trailing edge of a - trailingEdgeDevice is the trailing edge of the wing. This is also - valid for kinks that are present in the wing but not explicitly - modeled in the control surface. - The edges of the control surface within the wing are a - straight line in absolute coordinates! Hence, there needs to be a - straight connection between the eta-wise outer and inner points - of the edge that is within the wing in absolute coordinates. - - - - - - - - - - - Name of the trailing edge device. - - - - - - Description of the trailing edge device. - - - - - - UID of the parent of the TED. The parent can - either be the uID of the componentSegment of the wing, or the - uID of another TED. In the second case this TED is placed within - the other TED (double slotted flap). In this way n-slotted TEDs - can be created. - - - - - - - - - - - Definition of cruise rollers/mid-span stops. - Those features are small rolls at the leading edge of a flap - that keep the flap within the bending wing at cruise - configuration. - - - - - Definition of interconnection struts. Those - struts connect two neighbouring flaps and are load carrying in - case of an actuator of flap track failour. - - - - - Definition of z-couplings. Those elements - couple two neighbouring flaps in z-direction. - - - - - - - - - - - - - - - Trajectories - - - - - - - - - - - - - - - - - - - - - - Power breakdowns - - - - - - - - - - - - - - - - - - - Power breakdown case along a trajectory - - - - - - - - - - Name - - - - - Description - - - - - - - - - - - - - - - - trajectoryGlobalType - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - trajectoryType - - - - - - - - - - - - - - - - - - - - - - - - - - - 2D transformation - - - - - - - - - - - - - Scaling of the structural profile - - - - - - rotation around z-axis of profile definition - - - - - - translation of profile definition - - - - - - - - - - - - - - - Transformation - - - Transformation type, containing a set of - transformations. The order of the transformations is scaling - -> rotation -> translation, and they are executed in this - order. Any of them can be omitted; it will be replaced by its - defaults. - Transformations are always executed relative to the - child not the parent. I.e. a scaling does not have an influence - on the parent item. For example in the outer geometry of a wing - the element scaling does not influence the section. Scaling does - also not effect rotation and translation. - Scaling data default: 1,1,1. Those parameters - describe the scaling of the x-, y-, and z-axis. - Rotation data default: 0,0,0. The rotation - angles are the three Euler angles to describe the orientation of - the coordinate system. The order is always xyz in CPACS. - Therefore the first rotation is around the x-axis, the second - rotation is around the rotated y-axis (y') and the third - rotation is around the two times rotated z-axis (z''). - Translation data default: 0,0,0. Translations - can either be made absolute in the global coordinate system - (absGlobal) or absolute in the local Coordinate system (absLocal). - - - - - - - - - - - Scaling - - - - - Rotation - - - - - Translation - - - - - - - Rotation - - - - - Translation - - - - - - - Translation - - - - - - - - - - - - - - - Transformation - - - Transformation type, containing a set of - transformations. The order of the transformations is scaling - -> rotation -> translation, and they are executed in this - order. Any of them can be omitted; it will be replaced by its - defaults. - Transformations are always executed relative to the - child not the parent. I.e. a scaling does not have an influence - on the parent item. For example in the outer geometry of a wing - the element scaling does not influence the section. Scaling does - also not effect rotation and translation. - - - - - - - - - - Scaling data default: 1,1,1. Those parameters - describe the scaling of the x-, y-, and z-axis. - - - - - - Rotation data default: 0,0,0. The rotation - angles are the three Euler angles to describe the orientation of - the coordinate system. The order is always xyz in CPACS. - Therefore the first rotation is around the x-axis, the second - rotation is around the rotated y-axis (y') and the third - rotation is around the two times rotated z-axis (z''). - - - - - - Translation data default: 0,0,0. Translations - can either be made absolute in the global coordinate system - (absGlobal) or absolute in the local Coordinate system (absLocal). - - - - - - - - - - - - - - - transmissionGearRatioType - - - TransmissionGearRatio type, defining the ratio of - output rotation velocity to input rotation velocity. - - - - - - - - - - - - - - - - - - - - transmissionShaftInputsType - - - TransmissionShaftInputs type, defining the shaft inputs - of a transmission. - - - - - - - - - - - - - - - - - - - transmissionShaftInputType - - - TransmissionShaftInput type, defining a shaft input for - a transmission. - - - - - - - - - - - - - - - - - - - - transmissionShaftOutputsType - - - TransmissionShaftOutputs type, defining the shaft - outputs of a transmission. - - - - - - - - - - - - - - - - - - - transmissionShaftOutputType - - - TransmissionShaftOutput type, defining a shaft output - for a transmission. - - - - - - - - - - - - - - - - - - - - - transmissionsType - - - Transmissions type, containing all the - transmissions/gearboxes of a rotorcraft model. - - - - - - - - - - - - - - - - - - - transmissionType - - - Transmission type, defining a transmission/gearbox. - - - - - - - - - - - - - - - - - - - - - - - - - - Trim case - - - - - - - - - - - - - - Name - - - - - Description - - - - - UID of trim requirement - - - - - - - Description of the linear model - - - - - - - - - - - - - - Trim requirements - - - Contains a list of trim requirements - - - - - - - - - - - - - - - - - - - - Trim requirement - - - - - - - - Name - - - - - Description - - - - - UID of a predefined flight point - - - - - UID of weight and balance description - - - - - - - - - - - - - - - Trim - - - - Provides a list of trim cases - - - - - - - - - - - - - - - - - - - - Turbo generators - - - - - - - - - - - - - - - - - - - Turbo generator - - - - - - - - - - - - - - - UIDGroupDefinitionsType - - - - - - - - - - - - - - - - - - - - - - - UIDGroupDefinitionType - - - - - - - - - - - - - - - - - - - - - - - - - - - List of uIDs - - - - - - - - - - - Reference to a uID - - - - - - - - - - - - - - - - - - - - - Structural properties of the upper links, if existing. - The upper links do connect the upper forward part of the pylon - box with the forward wing attachment. - - - - - - - - - - - - - - - - - - - - - - List of segments that are allowed to be varied within a mission optimization. - - - - Provides a list of segments having variable conditions within the segmentBlock. - Example: a segmentBlock containing takeOff, climb, cruise, decent, landing segments has a cruise segment for which the range is variable. - The range of this segment is then to be calculated using the range defined for the segmentBlock while concerning the known ranges of all - other segments within the segmentBlock. - This concept needs to be practically tested. Does it suffice to mention (a list of) segments that are free to change to fit the overall block constraints? What happens if a segment is variable, though it has some constraints? When to define a segment as variable (climb until endPosition z, then endPosition x should be left free. Is the segment then variable? Probably not.). Somehow the 'free' segment should be in between fully defined segments (i.e.: a cruise+descent in between endPosition z == ICA and endPosition z == 0 for landing to define max range. How to define this exactly?) - - - - - - - - - - - - - - - - - - - variableSegmentType - - - - Containing the definition of variable segments for a segment block - - - - - - - - - - - defines uID of the segment having variable conditions - - - - - defines which condition(s) are variable within the segment (must be one of the defined - endConditions for the segmentBlock) - - - - - - - - - - - - - - - - - - - - Vehicles - - - - - The - vehiclesType - contains all vehicle-specific - data. - - - This includes the vehicle itself (i.e. - aircraft - and - rotorcraft - ). Furthermore, components - (e.g. - engines - , - structuralElements - , etc.) - as well as physical properties of - materials - and - fuels - can be predefined for easy and consistent reuse via - uID - -references. - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Version Informations - - - - - - - - - - - - - - - - - - - Version Information - - - - - - - - - - CPACS version of the dataset - - - - - - Description of CPACS dataset - - - - - - Timestamp of initial CPACS dataset creation - - - - - - Creator of initial CPACS dataset - - - - - - - - - - - - - - - - vtpFrameDefType - - - Definition of the individual VTP attachments - - - - - - - - - - Definition of tailplane attachment area - (Standard Configuration) - - - - UID of the fuselage frame at this VTP - attachment - - - - - Flag for option for VTP attachment between - defined FrameUID and the next one - - - - - UID of panel element at VTP attachment (shell - elements) - - - - - UID of structural element at VTP attachment - (base, beams) - - - - - UID of structural element at VTP attachment - (horizontal, beams) - - - - - UID of structural element at VTP attachment - (radial, beams) - - - - - - - - - - - - - - vtpInterfaceDefType - - - Definition of the interface of the VTP - - - - - - - - - Definition of the VTP interface - - - - - Definition of the VTP attachment frames and - their - reinforcement - - - - - - Defines area for valid x-position of VTP (just - used - if attachmentpoint is directly based on frame) ==> check and - potentially warning message - - - - - - Definition of the max. distance between - fuselage and - the defined VTP pins ==> check and potentially warning - message - - - - - - Definition of reinforcement area at VTP frame - positions (relative coordinate, smaller than - 1.0) - - - - - - Definition of vertical reinforcements at VTP - frame - positions (relative coordinate, smaller than - 1.0) - - - - - - value to change from horizontal to radial - reinforcements for VTP frame plates - - - - - - UID of elements to connect VTP pins with - fuselage - (beam elements) - - - - - - - - - - - - Definition of wall positions to place walls inside fuselage. - - - - - - - Wall position definition specifying a point in the fuselage to be connected to a wall segment. - - - - - - - - - - Definition of a wall position to place walls inside fuselage. - - - - - - - UID of a bulkhead determining the - x-coordinate of the position with the given - y- and z-coordinates. - - - - - - - UID of a wall segment determining the - x-coordinate of the position with the given - y- and z-coordinates. - - - - - - - UID of fuselage section determining the - x-coordinate of the position with the given - y- and z-coordinates. - - - - - - Absolute x-coordinate of wall position in fuselage coordinate system. - - - - - - Absolute y-coordinate of wall position in fuselage coordinate system. - - - - - Absolute z-coordinate of wall position in fuselage coordinate system. - - - - - - - - - - - - Reference to wall position uID. - - - - - - - - - - - - - Wall segment definition. - - - - - - - - - - - - - Defines extrusion direction. Rotation angle - around fuselage x-axis of extrusion direction. A - value of 0deg means fuselage z-axis as extrusion - direction. Default: 0.0deg. - - - - - - - - - - - - - - By default, the wall is only extruded in positive direction. If doubleSidedExtrusion is true, the wall is additionally extruded in negative direction as well. Default: false. - - - - - Rotates the first edge of the wall segment so that it is adjacent with the structural element defined in the first wall position (bulkhead, fuselage section or another plane wall). Default: false. - - - - - Rotates the last edge of the wall segment so that it is adjacent with the structural element defined in the last wall position (bulkhead, fuselage section or another plane wall). Default: false. - - - - - - A list of uIDs referencing other - structural/geometric elements that shall serve - as a boundary of the wall element. Possible - references are floor, wall or - genericGeometryComponent. A major requirement is - that the referenced element has an intersection - with the wall for at least the distance between - two wall positions. So that a full geometric - face of the wall is bounded by it. Neighbouring - wall faces that are not completely bounded by - the reference element are not affected. - - - - - - - Reference to the structural property definition - of this wall segment. - - - - - - - List of wall position uIDs that are used for - this wall segment. At least two positions must - be defined (for start and end position of wall). - If more than two positions are referenced here, - the wall is constructed out of several planar - faces that connect two consecutive positions - (Note: Order of position uIDs defines - connectivity). - - - - - - - - - - - - - - - Definition of wall positions to place - walls inside fuselage. - - - - - - - List of wall segments. - - - - - - - - - - - - - - webType - - - - SparWeb type, containing the cross section area of the - spar web and the material properties. - Please find below a picture where all spar cross - section parameters as well as the orientation references for - the material definition can be found: - - - - - - - - - - - - - - Material definition of the spar web. - - - - - - relPos ranges from 0 to 1 It defines the - position of the web relative to the caps (see picture below).. - - - - - - - - - - - - - - weightAndBalanceCaseType - - - WeightAndBalanceCase type, containing weight and - balance data for one case - - - - - - - - - - - - - - - - - - - - - - - - - weightAndBalanceFuelInTanksType - - - - - - - - - - - - - - - - - - - - - - weightAndBalanceFuelInTankType - - - - - - - - - - - - - - - - - - Ranges from 0 for empty tank to 1 - - - - - - - - - - - - - - weightAndBalanceFuelType - - - - - - - - - - - - - - - - - - - - - - - - - weightAndBalancemCargosType - - - For a higher ganularity it is possible to add more - information on the actual Cargo that are included in the - operational case. Please note that the information needs to be - identical with the massBreakdown. Hence, only links via uIDs can - be specified. - - - - - - - - - - - - - - - - - - - - - - weightAndBalancemPaxxType - - - For a higher ganularity it is possible to add more - information on the actual Pax that are included in the - operational case. Please note that the information needs to be - identical with the massBreakdown. Hence, only links via uIDs can - be specified. - - - - - - - - - - - - - - - - - - - - - - weightAndBalancePayloadType - - - - - - - - - - - - - - - - - - - - - - - - - - Weight and balance - - - WeightAndBalance type, containing weight and balance - datasets - - - - - - - - - - - - - - - - - - - - Definition of the landing gear wheel. - - - The center plane of the wheel is located on the end point of the axle. - - - - - - - - - - Wheel radius - - - - - With of the wheel - - - - - Brake: false = - not braked; true = braked. - - - - - - - - - - - - - - windowAssemblyPositionType - - - WindowAssembly type, containing an the position of a - windows assembly - - - - - - - - - - UID of the window element to be used - - - - - - x position of window element on global x axis - - - - - - z position of window element reference point - - - - - - angle around global x axis to define window - position with respect to positionX and postionZ - - - - - - - - - - - - - - - windowsAssemblyType - - - WindowsAssembly type, containing an assembly of windows - - - - - - - - - - - - - - - - - - - - windowsType - - - Windows type, containing windows - - - - - - - - - - - - - - - - - - - - wingAeroPerformanceType - - - wingAeroPerformance type, containing performance maps - with aerodynamic data of a wing. - - - - - - - - - - Reference to the uID of the analysed wing - - - - - - References used for the calculation of the - force and moment coefficients of the wing (in the wing axis - system!) - - - - - Calculated aerodynamic performance maps of the - wing - - - - - - - - - - - - - wingAirfoilsType - - - WingAirfoils type, containing wing airfoil geometries. - See profileGeometryType for further documentation - - - - - - - - - - - - - - - - - - - Position of the landing gear on a wing - - - - Definition of the position of the landing gear - (intersection point of main strut and pintle sturt) on a wing, - using relative componentSegment coordinates - - - - - - - - - - Relative height of spar or rib at which landing gear is attached. - - - - - - Relative spanwise position (eta) of spar at which landing gear is attached. - - - - - Relative chordwise position (xsi) of the rib at which landing gear is attached. - - - - - - - - - - - - - Cells of the wing. - - - WingCells type, containing all the cells of the wing. - - - - - - - - - - - - - - - - - - - - Cell of the wing - - - - A cell defines a special region of the wing. Within - this region skin and stringer properties can be defined that - differer from the properties of the rest of the wing. In general - a cell is defined by defining four borders – the cell leading - and trailing edge and the inner border and the outer border. - Those borders can either be defined by using eta/xsi coordinates - or by referencing to spars and ribs. Mixed definitions (e.g. - forward border is defined due to a spar, side borders due to eta - coordinates) is allowed. In general a cell is quadrilateral. But - if e.g. the spar, which is used for the definition of the - trailing edge, has a kink, the cell can have more than four - corners. - The cell leading and trailing edge (= forward and rear - border) can either be defined by referencing to a spar - (->sparUID) or by the defining the xsi (=relative chord) - coordinates of the border (xsi1 = inner end; xsi2 = outer end). - - The cell inner and outer border can either be defined - by referencing to a rib (->ribDefinitionUID and ribNumber) or - by the defining the eta (=relative spanwise) coordinates of the - border (eta1 = forward end; eta2 = rear end). - Some examples for wing cells can be found in the - picture below: - - - - - - - - - - - - - - - - - - - - - - - - - - - - - Structure of the wing - - - wingComponentSegmentStructure type, containing the - whole structure (skins, ribs, spars...) of the wing. - - - - - - - - - - - - - - - - - - - - - - - - CutOuts of the wing - - - - - - - - - - - - - - - - - - - CutOut of the wing - - - - A wing cutout is defined using any combination of eta-xsi-spar-rib-uids. - It has the similar syntax to a wingCell. - - The cell leading and trailing edge (= forward and rear - border) can either be defined by referencing to a spar - (->sparUID) or by the defining the xsi (=relative chord) - coordinates of the border (xsi1 = inner end; xsi2 = outer end). - - The cell inner and outer border can either be defined - by referencing to a rib (->ribDefinitionUID and ribNumber) or - by the defining the eta (=relative spanwise) coordinates of the - border (eta1 = forward end; eta2 = rear end). - Some examples for wing cells can be found in the - picture below: - - - - - - - - - - - - - - - - - - Type of the cutout (upper|lower|both): upper shell, lower shell or both. - - - - - - - - - - - - - - - - - - - - - - - - Elements of the wing. - - - WingElements type, containing the elements of a wing - section. - - - - - - - - - - - - - - - - - - - Element of the section. - - - - Within elements the airfoils of the wing are defined. - Each section can have one or more elements. Within each element - one airfoil have to be defined. If e.g. the wing should have a - step at this section, two elements can be defined for the two - airfoils. - Mathematically spoken a element is a coordinate system - that is translated, rotated and scaled relative to the section - coordinate system. This transformation parameters are defined - within the transformation section. The wirfoil, which is linked - by using the parameter airfoilUID is directly 'copied' in the - element coordinate system. If e.g. the airfoil is defined from 0 - to 1 in x-direction and the total scaling of the elements x-axis - equals 3.5 the wing chord is 3.5 m long. - An example for wing element can be found in the - picture below: - - - - - - - - - - - - - - Name of the wing element. - - - - - Description of the wing element. - - - - - - Reference to a wing airfoil. - - - - - - - - - - - - - - - - Border of the fuel tank (either rib or spar). - - - - - - - - - - - - - - Spar uID of the bordering spar. - - - - - - - UID of the rib set of the bordering rib. - - - - - - RibNumber of the rib set of the bordering - rib. - - - - - - - - - - - - - - Definition of the geometry of the wing fuel tank by - defining a continouse list of borders. - - - - - - - - - - - - - - - - - - - - - - List of wing fuel tanks. - - - - - - - - - - - - - - - - - - - - - - Definition of one wing fuel tank. - - - - - - - - - - - - - Name of the wing fuel tank. - - - - - - Description of the wing fuel tank. - - - - - - - - - - - - - - - - - Definition of the wing-fuselage attachment. - - - Definition of the wing-fuselage attachment - - - - - - - - - - - - - - - - - - - Definition of the wing-fuselage attachment - - - - Definition of the wing-fuselage attachment. The area - of the fuselage attachment (resp. center wing box, CWB) is - defined by defining one resp. two ribs from the rib definition. - If one rib is defined (rib1) the CWB goes from the closer end of - the componentSegment (e.g. wing symmetry plane) to the defined - rib. If two ribs are defined (rib1 and rib2), the CWB is between - both ribs. - Additionally attachment pins can be defined. At those - positions the wing is attached to the fuselage. This can be e.g. - used for defining the wing-attachment of high wing - configurations, HTPs or VTPs. - - - - - - - - - - - Definition of first (=inner) rib of the - fuselage attachment. - - - - - Definition of the second (=outer) rib of the - fuselage attachment. Optional. Only to be used if attachment is - defined over two ribs. - - - - - Definition of position, orientation, materials - and blocked DOFs of attachment pins. - - - - - Definition of actuators (e.g. trim actuator of - an HTP) of the attachment. - - - - - - - - - - - - - wingInterfaceDefinitionsType - - - CenterFuselage high wing interface definitions - - - - - - - - - - - - - - - - - - - - - - - - - centerFuselageMainFramesType - - - High wing main frame definition, containing mainframe - UIDs - - - - - - - - - - - - - - - - - - - - - wingInterfaceSupportStrutsAssemblyType - - - wingInterfaceSupportStrutsAssembly type, containing - support struts assembly - - - - - - - - - - - - - - - - - - - - wingInterfaceSupportStrutType - - - wingInterfaceSupportStrut type, containing support - strut definition - - - - - - - - - - Name of support strut. - - - - - Type description: lateral or longitudinal - support strut. - - - - - - - - - - - - - - - - - - IntermediateStructure cells - - - Definition of the intermediateStructure of the - componentSegment of the wing. - - - - - - - - - - - - - - - - - - - Definition of the cell of the intermediateStructure - - - - - IntermediateStructure: - It defines the filling materials between the upper and - lower shell (e.g. honeycombe structures in a smeared - representation). IntermediateStructure is optional.The position - of the intermediateStructure is defined in so called cells (= - special areas on the wing). Default is no intermediateStructure. - - Material Definition of intermediateStructure: - - The material of the intermediateStructure is reference - by 'material'. The material orientation is defined by 'rotX' and - 'rotZ'. 'rotZ' is defined equivalent to the stringer angle resp. - the skin orthotropyDirection. 'rotX' equals a positive rotation - around the wings x-axis, while a rotation of zero is equivalent - to the wing middle plane. - A picture to clarify the reference direction of rotZ - (equivalent to orthothropy direction of the wing) can be found - in the picture below: - - - - Position definition by using cells: - A cell defines a special region of the wing. Within - this region the cell properties are defined. In general a cell - is defined by defining four borders – the cell leading and - trailing edge and the inner border and the outer border. Those - borders can either be defined by using eta/xsi coordinates or by - referencing to spars and ribs. Mixed definitions (e.g. forward - border is defined due to a spar, side borders due to eta - coordinates) is allowed. In general a cell is quadrilateral. But - if e.g. the spar, which is used for the definition of the - trailing edge, has a kink, the cell can have more than four - corners. - The cell leading and trailing edge (= forward and rear - border) can either be defined by referencing to a spar - (->sparUID) or by the defining the xsi (=relative chord) - coordinates of the border (xsi1 = inner end; xsi2 = outer end). - - The cell inner and outer border can either be defined - by referencing to a rib (->ribDefinitionUID and ribNumber) or - by the defining the eta (=relative spanwise) coordinates of the - border (eta1 = forward end; eta2 = rear end). - Some examples for wing cells can be found in the - picture below: - - - - - - - - - - - - - - - - - - Reference to the material of the intermediate - structure. - - - - - 'rotX' equals a positive rotation around the - wings x-axis, while a rotation of zero is equivalent to the wing - middle plane direction. - - - - - 'rotZ' is defined equivalent to the stringer - angle resp. the skin orthotropyDirection. - - - - - - - - - - - - - - Definition of a ribCell - - - RibCells are optional elements. They are defined via a - fromRib and a toRib. The enumeration is within the ribSet. - RibNumber 1 starts at etaStart. - - - - - - - - - - Defines the beginning of the ribCell. The - enumeration is within the ribSet. - - - - - Defines the ending of the ribCell. The - enumeration is within the ribSet. - - - - - WING: The Rotation along the x describes a - rotation around a line, that is defined by the intersection of - the rib with the wing middle plane (orientated from leading to - trailing edge). This angle defaults to 90° which means, that the - rib is perpendicular on the wings middle plane. PYLON: The - Rotation along the z describes a rotation around the pylons - z-axis (= rotation in top view). This angle defaults to 90° - which means, that the rib is perpendicular to the pylons x-axis. - - - - - - The orthotropyDirection is defined as rotation - around the ribs z-axis. The rib coordinate system is defined as - follows: x-axis is from leading to trailingeEdge of the - componentSegment in the direction of the rib elongation. z-axis - is normal to the rib in the direction of positive eta. y is - defined by right hand rule. Rotation is around the z-axis. Zero - degrees are at the x-axis positive direction. - - - - - - - - - - - - - - - - - Cross section properties of a wing rib - - - wingRibCrossSectionType, containing the definition of - ribsCrossSection - - - - - - - - - - The orthotropyDirection is defined as rotation - around the ribs z-axis. The rib coordinate system is defined as - follows: x-axis is from leading to trailingeEdge of the - componentSegment in the direction of the rib elongation. z-axis - is normal to the rib in the direction of positive eta. y is - defined by right hand rule. Rotation is around the z-axis. Zero - degrees are at the x-axis positive direction. - - - - - - WING: The Rotation along the x describes a - rotation around a line, that is defined by the intersection of - the rib with the wing middle plane (orientated from leading to - trailing edge). This angle defaults to 90° which means, that the - rib is perpendicular on the wings middle plane. The rotation - angle is defined at the intersection point of the rib with the - ribReference line. The rib itself is always straight and not - twisted. PYLON: The Rotation along the z describes a rotation - around the pylons z-axis (= rotation in top view). This angle - defaults to 90° which means, that the rib is perpendicular to - the pylons x-axis. - - - - - - - - Post element definition applied to all vertical intersections with spars - - - - - - - - - - - - - Explicit positioning of a wing rib - - - - Use this type for an explicit positioning of a rib. As opposed to - ribsPositioning, this defines a single rib connecting a specified start - and end point. - - - - - - - - - - - - - Defines the start of the rib defined in eta-xsi coordinates of a reference plane - - - - - - - Defines the start of the rib defined by a point on a reference curve - such as a spar, but not an explicit sparPosition - - - - - - - Defines the location of the beginning of the rib using a specific sparPosition. - - - - - - - - - Defines the end of the rib defined in eta-xsi coordinates of a reference plane - - - - - - - Defines the end of the rib given by a point on a reference curve - such as a spar, but not an explicit sparPosition - - - - - - - Defines the location of the end of the rib using a specific sparPosition. - - - - - - - - Defines the forward beginning of the ribs. It can either be a - sparUID or "trailingEdge" or "leadingEdge". - - - - - - - RibEnd defines the backward ending of the ribs. It can either be a - sparUID or "trailingEdge" or "leadingEdge". - - - - - - - - - - - - - - wingRibPointType - - - - The wingRibPointType is used to define reference points on ribs. - It can be used for rib set definitions (wingRibsPositioningType) as - well as explicit rib definitions (wingRibExplicitPositioningType). - - - - - - - - - - - - The UID of the rib definition. Can be a reference to nodes - of either wingRibsPositioningType or wingRibExplicitPositioningType. - - - - - - - For references of type wingRibsPositioningType this node indicates the rib number of the rib set. - If not given it defaults to 1. - - - - - - - Normalized xsi coordinate of the rib point which is measured along the rib - from the start point [0] towards the end point [1]. - - - - - - - - - - - - - - Wing ribs - - - RibDefinitions type, containing the definition of all - ribs of the wing. - - - - - - - - - - - - - - - - - - - Definition of a set of ribs - - - - RibDefinitionType, containing the definition for ribs. - Ribs are defined in sets of one or more ribs. The positions of - the rib, as well as the orientation of the ribs are defined in - 'ribPositioning'. The cross section properties, as e.g. - materials, are defined in 'ribCrossSection'. - - - - - - - - - - - Name of the rib set - - - - - Description of the rib set - - - - - - - - - - - - - - - - - - - - Positioning of a set of wing ribs - - - - The ribsPositioning type allows the definition of a set - of ribs which is distributed over a specified spanwise area. - The positions of the ribs are defined by placing the - ribs on a reference line on the wing (ribReference). The inner - and the outer beginning of the rib set is defined using etaStart - and etaEnd. The position of the forward and rear end of the ribs - is defined by ribStart and ribEnd. The orientation of the ribs - is defined in ribRotation. The number of ribs of the current rib - set is either defined by ribNumber or by spacing. - Three examples how ribs can be placed on the wing are - illustrated in the picture below. For more detailed information, - please refer to the description of each parameter. - - - - - - - - - - - - - - - - Defines the start of the rib defined in eta-xsi coordinates of a reference plane - - - - - - - Defines the start of the rib by a point on a reference curve, - such as a spar, but not an explicit sparPosition - - - - - - - Defines the location of the beginning of the rib using a specific sparPosition - - - - - - - - - Defines the end of the rib defined in eta-xsi coordinates of a reference plane - - - - - - - Defines the end of the rib defined by a point on a reference curve - such as a spar, but not an explicit sparPosition - - - - - - - Defines the location of the end of the rib using a specific sparPosition - - - - - - - - Defines the forward beginning of the ribs. It can either be a - sparUID or "trailingEdge" or "leadingEdge". - - - - - - - Defines the backward ending of the ribs. It can either be a - sparUID or "trailingEdge" or "leadingEdge". - - - - - - - - The spacing of the ribs defines the distance between two ribs, - measured on the - ribReferenceLine. First rib is placed at etaStart. - - - - - - - Defines the number of ribs in this ribSet. First rib is at - etaStart on the - referenceLine, last rib is at etaEnd. The spacing is constant on the - ribReferenceLine. - - - - - - - - The ribReference is the reference line for the computation of the rib set spacing. - It can either be a sparUID or "trailingEdge" or "leadingEdge" - - - - - - - - RibCrossingBehaviour can either be 'cross' or 'end'. If it is set to'end' the ribs - of this rib set will end at the intersection with another rib. - If it is set to - 'cross' the ribs of this rib set will continue at the intersection - with another rib. - - - - - - - - - - - - - - - - - - - - - - wingsAeroPerformanceType - - - wingsAeroPerformance type, containing - wingsAeroPerformance - - - - - - - - - - - - - - - - - - - Sections of the wing. - - - WingSections type, containing all the sections of the - wing. - - - - - - - - - - - - - - - - - - - Section of the wing. - - - - WingSection type, containing a wing section. The - sections contains elements, where the airfoils are defined. For - the definition of a wing at least two sections (root and tip) - have to be defined, but any number greater than 2 is also - possible. - Mathematically spoken a section is a coordinate system - that is translated, rotated and scaled relative to the wing - coordinate system. This transformation parameters are defined - within the transformation section. - In addition to the translation, which is defined in - the transformation part, the section can be translated by using - the positionings vectors (wing->positiongs). Translation of - the positionings vectors is added to the translation of the - section. - An example for wing sections can be found in the - picture below: - - - - - - - - - - - - - - Name of wing the wing section. - - - - - - Description of the wing section. - - - - - - - - - - - - - - - - - Segments of the wing. - - - WingSegments type, containing all the segments of the - wing. - - - - - - - - - - - - - - - - - - - Segment of the wing. - - - - A segment defines which two wing elements (=cross - sections) are linked to one wing segment. - An example for wing segments can be found in the - picture below: - - - - - - - - - - - - - - Name of wing the wing segment. - - - - - - Description of the wing segment. - - - - - - Reference to the element from which the - segment shall start. - - - - - Reference to the element at which the segment - shall end. - - - - - Optional and additional guidecurves to shape - the outer geometry. - - - - - - - - - - - - - - Shells of the wing - - - Within the wingShellType the upper and lower skin of a - and the skin stringers are defined. At 'skin' and 'stringer' the - skin and stringer properties of the complete componentSegment are - defined. If different skin or stringer properties should be - defined in a special region of the wing this can be done within - 'cells'. - If the stringer should not be defined explicitly, they - can be defined implizite by defining an equivalent material layer - and using a composite as material. - - - - - - - - - - - - - - - - - - - - - - Material properties of the wing skin. - - - - The wingSkinType describes the material properties of - the wing. - For composites materials: the positive z-direction is - from the outer side to the inner side. - For composites materials: the reference axis for the - orthotropyDirection is defined by the two leading edge points of - the 'from'- and the 'to'-element of the componentSegment - definition. The angle between the reference axis and the - orthotropyDirection equals the rotation around the z-reference - axis. For details, please refer to the picture below: - - - - - - - - - - - - - - - Material properties of the wing skin. - - - - - - - - - - - - - - Wing spars - - - - Spars type, a spar is defined by sparSegments that - stretch between multiple sparPositions. The spar definition is - very flexible in CPACS. Spars can start and end at any position - of the wing, spars can have kinks at any position of the wing - and spars can cross each other or merge. - At first the spar points (->sparPositions) have to - be defined. Spar points are defined using the relative - coordinates eta and xsi. Spar points do lay on wing middle - plane. - Two or more spar points are connected to on spar - segment (->sparSegments). Each spar segment can be seen as - one spar. The spar geometry between two spar points is defined - as a direct/straight connection in global coordinate system - and not in eta xsi coordinates of the component segment. - One spar point can be used by more than one spar, if - e.g. two spars are merging. The detailed cross section of the - spar is also defined with sparSegments. - Please find below a picture for an example definition - of 3 spars in one wing, by using spar position points and spar - segments: - - - - - - - - - - - - - - - - - - - - - - - - Definition of the wing stringers. - - - - Within the wingStringerType wing stringers are - defined. The stringer are defined by referencing on the - stringerStructureUID, where the shape and material settings of - one single stringer is defined. In addition the orientation and - the stringer pitch have to be defined: - One stringer intersects the point at the given xsi and - eta position. - - - - Alternatively, an explicit stringer definition can be - applied if the stringers shall be tapered. - - - - - - - - - - - - - This is the simple and default stringer - definition - - - - The pitch describes the distance between to - adjacent stringers in the plane rectangular to the stringer - elongation direction. - - - - - - Stringer angle: the reference axis for the - stringer angle is defined by the two leading edge points of - the 'from'- and the 'to'-element of the componentSegment - definition. The angle between the reference axis and the - stringers equals the rotation around the z-reference axis. For - details, please refer to the picture below. - - - - - - If the reference of the stringer angle shall - be different from the default implementation then this - parameter may be set. Allowed values include: leadingEdge, - trailingEdge and globalY. Furthermore, it is possible to - provide the UID of a spar. - - - - - - This is the explicit stringer definition. - Please note that for a consistent definition two out of the - possible three elements innerBorder (xsiLE, xsiTE), outerBorder - (xsiLE, xsiTE) and stringer angle (and angle reference) must be - defined. Any combination of two of the three is valid - - - - - The number of stringers; default is 0 - - - - - - Stringer angle: the reference axis for the - stringer angle is defined by the two leading edge points of - the 'from'- and the 'to'-element of the componentSegment - definition. The angle between the reference axis and the - stringers equals the rotation around the z-reference axis. For - details, please refer to the picture below. - - - - - - If the reference of the stringer angle shall - be different from the default implementation then this - parameter may be set. Allowed values include: leadingEdge, - trailingEdge and globalY. Furthermore, it is possible to - provide the UID of a spar. - - - - - Inner border xsi coordinate at the leading - edge of the stringer definition - - - - - Outer border xsi coordinate at the leading - edge of the stringer definition - - - - - Inner border xsi coordinate at the trailing - edge of the stringer definition - - - - - Outer border xsi coordinate at the trailing - edge of the stringer definition - - - - - - - - - - - - - - - wingStructuralMountsType - - - - - - - - - - - - - - - - - - - - - - Wings - - - Wings type, containing all the lifting surfaces (wings, - HTPs, VTPs, canards...) of an aircraft model. - - - - - - - - - - - - - - - - - - - Wing type, containing all a lifting surface (wing, HTP, - VTP, canard...) of an aircraft model. - - - - Wing type, containing all a lifting surface (wing, - HTP, VTP, canard...) of an aircraft model. - Position of the wing: The position of the wing is - defined using the transformation parameters. Using those - parameters, the wing coordinate system is translated, rotated - and scaled. - Definition of the wings outer shape: The outer shape - of the wing is defined by airfoils that are placed within the 3D - space. Two airfoils are combined to one wing segment within the - segments. For the definition of the positions of the airfoils, - different sections are defined. Within each section one or more - elements are defined. The airfoil shape is defined within the - elements. If the wings outer shape should e.g. have a step it is - possible to define two different airfoils in one section by - using two elements. In most cases each section will only include - one element. Positionings are vectors that are used for an - additional translation of the sections by using 'user friendly - paramaters' as e.g. sweep and dihedral. Please note, the first - positioning may be non-zero. Often it will be zero just to - locate the wing at the position stated by the translation, but - this is not necessary. Finally the wing segments are defined by - combining two consecutive elements. A more detailed description - is given within the different parameters. - Definition of control surfaces, wing structures, wing - fuel tank and wing fuselage attachment: those parts are defined - within componentSegments. Please refer to the documentation - there. - - - - - - - - - - - - - - Name of the wing. - - - - - Description of the wing. - - - - - UID of part to which the wing is mounted (if - any). The parent of the wing can e.g. be the fuselage. In each - aircraft model, there is exactly one part without a parent part - (The root of the connection hierarchy). - - - - - - - - - - - - - - - - - - - - The two elements that where the structural connection - is placed. - - - - - - - - - - - - - Element uID of the element of the CURRENT - componentSegment where the structural connection is placed. - - - - - - Element uID of the element of the second - componentSegment where the structural connection is placed. - - - - - - - - - - - - - - Two spars that are structurally connected. - - - - - - - - - - - - - Spar uID of the CURRENT componentSegment. - - - - - - Spar uID of the second componentSegment. - - - - - - - - - - - - - - wingWingAttachmentsSparsType - - - - - - - - - - - - - - - - - - - - - - List of wingWingAttachments. - - - - - - - - - - - - - - - - - - - - - - wingWingAttachmentType - - - Definition of the structural connection between two - wings resp. two componentSegments. Note: All structural - connections between two wings/componetSegments have to be defined - using wingWingAttachments. The wingWingAttachment has only be - defined in one of the two componentSegments, that are connected. - - - - - - - - - - - UID of the componentSegment, that is connected - with the current one. - - - - - - - Defines if the upper shell of the current - componentSegment is structurally connected to the upper or lower - shell of the second componentSegment. Can have the values - 'upperShell' or 'lowerShell'. - - - - - - - - - - - - - Defines if the lower shell of the current - componentSegment is structurally connected to the upper or lower - shell of the second componentSegment. Can have the values - 'upperShell' or 'lowerShell'. - - - - - - - - - - - - - - - - - - - - - xsiIsoLineType - - - Iso line described by point of same xsi coordinate. - Can be either segment or component segment coordinates. - - - - - - - - - - Relative spanwise position. Xsi refers to the segment or componentSegment depending on the referenced uID. - - - - - This reference uID determines the reference coordinate system. - If it points to a segment, then the eta value is considered to be in segment - eta coordinate; if it points to a componentSegment, - then componentSegment eta coordinate is used. - - - - - - - - - - - - - zCouplingsType - - - - - - - - - - - - - Definition of one z-coupling. - - - - - - - - - - - - - - zCouplingType - - - - - - - - - - - - - Reference to the control surface that is - connected to this control surface by the z-coupling.. - - - - - - Material of the movable part of the - z-coupling. - - - - - Definition of the attachment of the z-coupling - to this control surface. - - - - - Definition of the attachment of the z-coupling - to the other control surface. - - - - - - - - - + + + + + + + + + + + + + + + + + + + + CPACS root element + + + + + Version + + V3.5-beta + + Date + + 2023-08-06 + + + + 1. Overview + + + The + C + ommon + P + arametric + A + ircraft + C + onfiguration + S + cheme + (CPACS) + is an XML-based data format for describing aircraft configurations and their corresponding data. + + + This XMfL-Schema document ( + XSD + ) serves two purposes: (1) it defines the + CPACS + data structure used in the + XML + file (e.g., aircraft.xml) and + (2) it provides the corresponding documentation (see picture below). An XML processor (e.g., + + TiXI + https://github.com/DLR-SC/tixi + + or + XML tools in Eclipse) parses the XSD and XML files and validates whether the data set defined by the user (or tool) conforms to the given structure defined by the schema. + + + + + + This documentation explains the + elements + defined in + CPACS + and its corresponding + data types + . + Data types can either be + simple types + (string, double, boolean, etc.) or + complex types + (definition of attributes and sub-elements to build a hierarchical + structure). In addition, the sequence of the elements and their occurrence is documented. + + + To link the XML file to the XSD file, the header of the XML file should specify the path of the schema file. + An example could look like this: + + + ]]> + + + + CPACS is an open source project published by the + + German Aerospace Center (DLR e.V.) + https://www.dlr.de/ + + . For further information please visit + + www.cpacs.de + https://www.cpacs.de + + . + + + + + 2. Data structure + + + CPACS data is modeled in a hierarchical structure whose underlying concept follows a top-down description of a system-of-systems which decomposes a generic concept (e.g., an + aircraft + or + rotorcraft + ) into a more detailed description of its components. This originates from the conceptual and preliminary design of aircraft, where the level of detail is initially low and continues to increase as the design process progresses. + + + For some concepts within + CPACS + , however, a bottom-up approach is applied where the components are first defined in detail (sometimes referred to as + library + ) and then linked within an instantiated higher-level concept. This is advantageous when used multiple times within complex systems, such as + engines + , which only have to be defined once in order to be referenced several times on the + aircraft + . The combination of these two methodologies is known as middle-out approach and enables the goal to fully parametrize aeronautical systems. + + + + + + + + 3. Coordinate Systems + + + 3.1. CPACS coordinate system + + + Coordinate systems are a regular cause for ambiguous interpretation of data. In + CPACS + , the reference coordinate system is the + CPACS + -coordinate system. This coordinate system is used for most of the data. A single exception is made in order to keep aerodynamic data in an aerodynamic coordinate system. The following paragraphs outline the determination to known coordinate systems. + + + The + CPACS + coordinate system is the coordinate system identified by + + TiGL + https://dlr-sc.github.io/tigl + + , + CPACS + 's geometric library. It is a right-handed coordinate system. If an aircraft is defined in the + CPACS + coordinate system it will usually follow the directions listed in the table below. + + + Therefore, the + CPACS + coordinate system can be confused with the body-fixed coordinate system. While often the + CPACS + coordinate system and the body-fixed coordinate system overlap, this must not always be true. Several definitions for body-fixed coordinate systems exist (x-axis through nose and tail, x-axis perpendicular to nose plane). For non-symmetric aircraft, body-fixed coordinate systems become even more complicated. Hence, analysis tools should stick to the + CPACS + -Coordinate system. It remains to the designer to model the geometry accordingly. + + + The + CPACS + coordinate system does not rotate with flow. Hence, aerodynamic calculations do rotate their flow relative to the + CPACS + -coordinate system. If not stated explicitly different, e.g. for target lift-coefficients, results are returned in the + CPACS + coordinate system, i.e. the cfx-coefficient is parallel to the + CPACS + x-Coordinate, regardless of the way the geometry is defined. + + + The following table gives a "best-practice" advice on how to locate a geometry within + CPACS + . Different approaches are, of course, valid as well. + + + + + Axis + + + Direction + + + Description + + + + x + tailwards + from nose to tail + + + y + spanwise + from symmetry plane to the right wingtip + + + z + upwards + from landing gear to tip of vertical tailplane + + + + The following figures show an example of a geometry that is aligned with the + CPACS + coordinate system, i.e. the body-fixed coordinate system corresponds to the + CPACS + coordinate system. + + + + + + The aerodynamic analysis is relative to the + CPACS + coordinate system. That is, the angle of attack is represented by the dashed orange line. Results of the aerodynamic calculation are given in the + CPACS + coordinate system. + + + + + + The following figures give an example of a geometry that is not defined in alignment with the + CPACS + coordinate system. It is a valid + CPACS + file, but only used in this example for demonstrative purposes. + + + + + + The body axes and the + CPACS + coordinate system do not align. That is, the origin of the geometry is not at + CPACS + (0,0,0) but at a point in positive x- and z-direction. + + + + + + Again, the aerodynamic analysis is relative to the + CPACS + coordinate system. That is, the angle of attack is represented by the dashed orange line. Results of the aerodynamic calculation are given in the + CPACS + coordinate system. + + + 3.2. Local coordinate systems via parentUID and transformation + + + Some elements in + CPACS + , in particular the geometric components, are described in local coordinates. + The hierarchical data structure allows to define a local coordinate system either with respect to the coordinate system of the parent element or with respect to the global + CPACS + coordinate system. + This is achieved by combining the two elements + parentUID + and + transformation + : + + + + + parentUID + : An individual data hierarchy can be set up using the optional + parentUID + element. + Here it is + + important that exactly one element does not contain the + parentUID + + in order to identify the top element of this user-specific hierarchy. + As soon as the + parentUID + (which refers to the + uID + of the parent element) is set, a local coordinate system of the corresponding node is instantiated. + + + + + transformation + : This allows the coordinate system to be transformed via + translation + , + rotation + and + scaling + . + As soon as the + parentUID + is set, this transformation refers to the local coordinate system (in the current + CPACS + version this only affects + translation + ). + An attribute + refType + is used to either make this explicit ( + refType="absLocal" + ) or to override this and reference the global CPACS coordinate system instead ( + refType="absGlobal" + ). + + + + + The following table summarizes the possible combinations of + parentUID + and + transformation + and the resulting coordinate system (local or global): + + + + + + parentUID + not set + + + parentUID + set + + + + + transformation + without + refType + + global + local + + + + transformation + with + refType="absLocal" + + global + local + + + + transformation + with + refType="absGlobal" + + global + global + + + + Note: + The combination of + transformation + with + refType="absLocal" + and no + parentUID + is global, because the local coordinate system to which the transformation is referring to via + refType + equals the global coordinate system (see fuselage in the following example). + + + An exemplary use case further illustrates the concept of the coordinate system hierarchy. + The + CPACS + schema shall not specify in advance that a wing is always be part of the fuselage and engines must always be part of the wing. + In other cases the engine could be attached to the fuselage, which would not be possible via a predefined XML tree. + The following figure shows how components of the aircraft are related to each other via the + parentUID + . + The fairing is a child of the wing and is therefore automatically translated when the wing is translated. + Likewise, the horizontal tailplane is a part of the vertical tailplane and is therefore affected by translation of the latter: + + + + + + + + 4. Units + + + There are no explicit attributes describing units in + CPACS + . The general convention is that all values must be given in the following SI-units: + + + + [m] + Position, Distance + + + + [m + 2 + ] + + Area + + + + [m + 3 + ] + + Volume + + + [kg] + Mass + + + [s] + Time + + + [K] + Temperature + + + or in derived units, e.g.: + + + [N] + Force + + + [Nm] + Moment + + + [W] + Power + + + [J] + Energy + + + + The only non SI unit used throughout + CPACS + is the angle in degrees [°]. + For the sake of an intuitive use the angles are given in degrees rather than in radian [rad]. + + + + [°] + Angle + + + + + + + 5. Splitting up a + CPACS + dataset into several files + + + + To provide a better overview, it is possible to split up a + CPACS + dataset into several files. This can be done by inserting an + <externaldata> + node at an arbitrary position into the dataset. This node contains a + <path> + node with a URI to the external file(s), followed by one or more + <filename> + nodes, containing each a name of a file to be included at that position. Below, an example of such external data is given: + + + + + + + + + file:://airfoils + NACA0010.xml + NACA2412.xml + + + NACA 0012 Airfoil + ... + + + + + + ]]> + + + Such an external file would look like: + + + + NACA 0010 Airfoil + ... + + ]]> + + + The file would be included completely, except for its title line + <?xml version="1.0" encoding="utf-8"?> + . This concept can also be used recursively (external files of external files), but it is important to prevent circle connections (file "A" loading file "B" loading file "C" loading again file "A" ...). + + For path URI addresses, the trailing file separator "/" may be omitted. Below, some examples for path URIs are given: + + + Absolute local path: + file:///tmp + or + file:///c:/windows/tmp + + + Relative local directory: + file://relativeDirectory + or + file://../anotherRelativeDirectory + + + Remote net resource: + http://www.someurl.de + + + + With the help of the + Ti + XI + X + ML + I + nterface + + + TiXI + https://github.com/DLR-SC/tixi + + + , a + CPACS + dataset that is split into multiple files can be reassembled into a single tree structure for subsequent validation against the + CPACS + schema. The following commands are used to link external data sets: + + + + <externalFileName> + : Name of the external data file + + + <externalDataDirectory> + : Directory of the external data file. Its content is analogous to the + externaldata + 's + path + -element described above. + + + <externalDataNodePath> + : + + XPath + https://www.w3schools.com/xml/xpath_intro.asp + + of the node which is replaced with the content of the external file. In case that it is an external file of an external file, then it is the + XPath + in the outer external file. If, e.g., in the example above the + pointList + element would have also been loaded from an external file, then the entry would just be: + externalDataNodePath="/airfoil" + . This is used primarily for loop-detection. + + + The merged data tree for the example above would look like: + + + + + + + + NACA 0010 Airfoil + ... + + ... + + NACA 0012 Airfoil + ... + + + + + + ]]> + + + + + 6. UIDs and references + + + The + CPACS + -dataset often uses references between nodes. Typically, these + references define connections between elements which are located somewhere else in the hierarchical dataset (e.g. a + wing + is connected to a + fuselage + ; a specific + engine + is connected to a + pylon + ; etc.). These connections are defined by + unique identifiers + (uID) which are specified as attributes. Thus, there are elements which can be referenced via a + uID + attribute, e.g. a fuselage: + + ... + ]]> + + + + as well as elements which refer to the former, e.g. a wing pointing to its geometrical parent: + + + ATTAS main wing + ATTAS_fuselage + ... + ]]> + + + + In previous + CPACS + versions, referencing elements were identified via the + isLink="True" + attribute. Since this is superfluous due to the explicit definition of the element properties via the + CPACS + schema, this attribute no longer needs to be listed. It is nevertheless a valid optional attribute to ensure compatibility with older datasets, but might be removed in future versions. + + + Since + uID + s are only used to link nodes within the XML file, no naming convention is required. The characters only have to conform to the conventions of the + + xsd:ID + http://books.xmlschemata.org/relaxng/ch19-77151.html + + type standardized by the + + W3C + https://www.w3.org/ + + . + UIDs, however, must be unique! + Although a common practice for naming + uID + s is their position in the data hierarchy (e.g. + uID="mainWingSection3" + ), + uID + s as shown in the above example are absolutely valid as well. It is therefore recommended to use the + name + element + to convey human-readable meanings. + + + + + + 7. Usage of + name + , + description + and + uID + + + + CPACS is designed to serve as a central data exchange format in fully automated process chains. + A key requirement is therefore that tools can automatically read and process an incoming CPACS file. + A second requirement is that users can interpret the data set. + To address both requirements, the following usage of the + name + and + description + elements in combination with the + uID + attribute is proposed: + + + + + name + : A specification of the + name + element is usually mandatory for sequences of elements (e.g., if max occurrence is unbounded + [1..*] + ). + Typical examples are + wings/wing + , + aeroPerformance/aeroMap + or + missions/mission + . + Such elements must be able to be listed by tools, especially for visualization and reporting purposes, where the + name + element serves as a + concise and human-readable + indicator of the actual meaning of the corresponding element in the list (e.g., which + wing + , which + aeroMap + , which + mission + ). + This is usually a single word or a small number of words. + + + + + description + : This element is usually optional and is used to add + comprehensive and human-readable + explanations. This is usually at least one explanatory sentence. + + + + + uID + : As described in more detail in Section 6, the + uID + attribute is mainly used for internal referencing of CPACS elements. + Further processing software, e.g. + TiXI + and + TiGL + , also use the + uID + s to improve the robustness of the data query. + Consequently, the + uID + attribute serves as a + machine-readable + indicator and does not claim to be interpretable by human users. + In some practical use cases, the same string is chosen for + uID + and + name + . + However, restrictions on the choice of characters for the + uID + attribute must be considered, for example that no spaces may be used and the + uID + must be unique. + + + + + + Main wing + This is the main wing which was designed by my awesome wing sizing design tool. Your tool should not try to read and interpret what I'm writing here as typos are not recognized by XML processors. + + ]]> + + + + + 8. Symmetry + + + 8.1. Specification of symmetric elements + + + Sometimes it might be useful to specify a part of the aircraft as symmetric instead of holding all the data twice in nearly identical form in the dataset (e.g. left and right wing are usually identical, except for the sign of the y-coordinate). + Hence, some parts offer the option to set a + symmetry + attribute: + + + + ]]> + + + There are six possible attribute values: + + + x-y-plane + : Symmetry w.r.t. the x-y plane of the + CPACS + coordinate system + + + x-z-plane + : Symmetry w.r.t. the x-z plane of the + CPACS + coordinate system + + + y-z-plane + : Symmetry w.r.t. the y-z plane of the + CPACS + coordinate system + + + inherit + : Symmetry inherited from parent element (default behavior, i.e. also applies if attribute not set) + + + none + : Symmetry inheritance from parent element disabled + + + Note + : It must be taken from the documentation of the respective element which of these attribute values may be set. + + + One example of how to apply the + symmetry + attribute is shown in Sec. 3.2. Another simplified example shown below illustrates the combination of different symmetry properties of 4 wings: + + + + + + + Wing 1 + is mirrored on the x-z plane. + + + Wing 2 + has wing 1 as parent element, but suppresses its symmetry inheritance. + + + Wing 3 + has wing 2 as parent element and sets a new symmetry at the x-y plane. + + + Wing 4 + has wing 3 as parent element and no symmetry attribute specified. Thus, it inherits the symmetry at the x-y plane from wing 3. + + + + Note + : The corresponding transformations are not shown here. + + + 8.2. Referencing symmetric elements + + + All nodes (e.g., + parentUID + ) in + CPACS + that refer to a component holding the symmetry attribute (e.g., wing) might also have a + symmetry + attribute to specify how symmetry is propagated through the resulting element hierarchy. + + + The + symmetry + attribute of a referencing element may take three values: + symm + , + def + , + full + : + + + def: + The element refers to the geometric component that has a + symmetry + attribute and refers only to the defined side of the geometric component. + + + symm: + The element refers to the geometric component that has a + symmetry + attribute and refers only to the symmetric side of the geometric component. (Similar to the previous _symm solution) + + + full: + The element refers to the geometric component that has a + symmetry + attribute and refers to the complete component. (This is the default behaviour) + + + + + + + For example, to refer to the "other" side of a mirrored wing the following the following syntax might be used: + + + + wing + ]]> + + + Note: This feature is not implemented in TiGL. The upper figure is manually processed to illustrate the principle. In addition, there is an ongoing debate whether the approach is suitable for CPACS due to rapidly increasing complexity and unresolved implicit assumptions as to whether it is one or two components after mirroring. Therefore, it is advised to avoid using the symmetry attribute if possible. + + + + + 9. Vectors and arrays + + + For large data sets (e.g. increments of aerodynamic coefficients due to control surface deflections) it is advantageous + to map them via vectors and arrays instead of using a sequence of nodes for each data value. Therefore vectors and arrays are defined as semicolon-separated lists in + CPACS + . Via the documentation (derived from the XSD) of the corresponding nodes it has to be checked whether it is a vector or an array. + + + Vector + The vector is meant as a one-dimensional-array. In such a node, the values are given in a semicolon separated list: + + 0.;1.5;3.;4.5;6;7.5;9. + ]]> + + + + Array + + As for vectors, multi-dimensional arrays provide values in a semicolon separated list. An array is always preceded by a sequence of vectors, containing the dimensions and index values. Which vectors of an array are dimensioning is specified in the respective documentation of the array. + + + 1000.;2000.;3000. + + + InnerWingFlap + -1;-0.5;0;1 + + 11.;12.;13.;14.;21.;22.;23.;24.;31.;32.;33.;34. + ]]> + + + + Values for cl increments: + + + + Control parameter = -1 + Control parameter = -0.5 + Control parameter = 0 + Control parameter = 1 + + + Altitude = 1000m + 11. + 12. + 13. + 14. + + + Altitude = 2000m + 21. + 22. + 23. + 24. + + + Altitude = 3000m + 31. + 32. + 33. + 34. + + + + + + + + + + 10. Control Parameters + + Control parameters are abstract parameters, linking a generic floating point value to a certain status of a control device + (e.g. control surface, landing gear, suction system, brake parachute, ...). For control surfaces, such a data pair (control parameter + and control surface deflection status) is called a <step> and the ordered list of all steps for a control surface forms its deflection + <path>. + The control parameter values for each step are arbitrary floating point values. However, it is strongly recommended to use + values between -1. and +1., or between 0. And +1. (depending on the type of control surface). The smallest and the largest value implicitly + define the maximum deflection limits. It is mandatory, that the value “0.” is within the specified range, as this value is treated as + undeflected and used to specify a “clean” aircraft configuration (e.g. used in the clean aero performance map). It is recommended, but not + mandatory to specify a <step> with a <controlParameter> of 0. Consequently, no <controlParameter> must be used twice within + a single <path> definition. Deflection values between two specified steps are handled by linear interpolation. + The following example shows the usage of control parameters within a control surface deflection path definition: + + + + + ... + + ... + + + -1 + -20. + + + -0.5 + -10. + + + 0 + 0. + + + 1 + 5. + + + ... + ]]> + + + + + 11. Atmosphere + + + At some places in + CPACS + , an atmosphere has to be selected (e.g. for connecting an altitude with a certain pressure or density). + Currently, + CPACS + does only support a single atmospheric model: The ICAO Standard Atmosphere (ISA) from 1993 (see ICAO Doc 7488/3 'MANUAL OF THE ICAO STANDARD ATMOSPHERE', third edition, 1993) + It covers temperature, pressure, density, speed of sound, dynamic viscosity and kinematic viscosity with respect to altitude. + In + CPACS + , 'altitude' means what is called 'geopotential altitude' (H) in the ISA reference document and is given in [m]. + For details, see ISA manual, section 2.3, page E-viii f. + ISA covers a range from -5000 m to 80000 m. + + Temperature offsets are introduced on top of the definitions in the ISA manual (which does not cover such variations). The offset model + is based upon the idea that the pressure at a fixed geopotential altitude is independent from temperature offset (pressure altitude). + The temperature offset changes only the density (following rho = p / Gas Constant / T) (and viscosity, of course) + + + + CPACS 3.5-beta + + Release in August 2023 + + + new + headerType + and versioning strategy + + + cpacsVersion + marked as deprecated and moved to versionInfo node + + fix typos: + + various fixes in documentation + + airportCompatibility + + + mAdditionalCenterTanks + + + consistency + in + globalBeamPropertiesType + + + + capType + : add + uID + + + massBreakdown + + + + genericMassTyp + : add + componentUID + to link the corresponding components + + + mOperatorItemsType + : + + + + add + mAdditionalCenterTanks + + + add + mEngineAPUOils + + + add + mRemovableCrewRests + + + add + mToiletFluids + + + add + mUnusableFuels + + + add + mWaterReservoirs + + + add + mMiscellaneous + + + + align + mLandingGear + elements with more the new generic + landingGears + definition + + + + sparPositionType + : add + sparPositionCurve + (defines a spar position via a point on a curve) + + + isLink + attribute: marked as deprecated + + Systems definition + + + aeroMaps + + + + aeroLimitsIncrementMapType + : + controlDeviceUID + , ... --> + configurationDefinitionUID + + + aeroPerformanceBoundaryConditionsType + : + configurationType + --> + configurationDefinitionUID + + + aeroPerformanceIncrementMapType + : + controlDeviceUID + , ... -> + configurationDefinitionUIDs + + + + + + aircraftAnalysesType + + + + add + systemAnalyses + + + + + + aircraftModelType + + + + add + configurationDefinitions + + + add + systemArchitectures + + + + + + engineType + + + + add + rotors + + + + + + fuels + replaced by + chemicalEnergyCarriers + and + electricalEnergyCarriers + + + make sub-elements optional + + + + genericSystemType + : add + components + + + + operationalCaseType + + + + add + configurations + + + mPayload + optional + + + + + + vehiclesType + + + + add + systemElements + + + add + rotorElements + + + add + energyCarriers + + + + + + weightAndBalanceCaseType + + + + add + configurations + + + + + + aircraftModelType + + + + add + systemAnalyses/powerBreakdowns + + + + add cryogenic fuel storage + + add + ducts + definition + + hinge line definition aligned with TiGL + + fix wront type assignment in + costHydraulicSystemsType + + + wingWingAttachmentType + : + upperShellAttachment + and + lowerShellAttachment + restricted to + upperShell + and + lowerShell + + + add + wingCutouts + + + add + fuselageStructuralMountsType + + add CI schema validation + add python script for automatic syntax formatting + add automatic generation and publication of html documentation via GitHub actions and Appveyor + + + + + CPACS 3.4 + + Release in April 2022 + + + Revision of + decks + definition ( + compatibility break + ) + + + Mass breakdown: add + mSparSkins + and + mSparCells + to + mSpar + + + Mass breakdown: fix hierarchical error in + mMiscellaneous + ( + compatibility break + ) + + + Mass breakdown: fix typo in + mPylon + ( + compatibility break + ) + + + Nacelle guide curves: set + description + optional + + + Mission definition: add + uID + to elements in + geographicPointConstraintType + + + Mission definition: add + powerFraction + , + powerRemaining + and + powerConsumed + to + missionSegmentEndConditionType + + + Mission definition: rename + referenceEndCondition + to + referenceEndConditionUID + in + constraintSettingsType + ( + compatibility break + ) + + + Mission definition: rename + reqClassification + to + requirementClassification + in + flightPerformanceRequirementType + ( + compatibility break + ) + + Add contour coordinates for cell definition + Add vehicle independent node for external geometry + + Remove + paxFlow + element from + aircraftAnalysesType + ( + compatibility break + ) + + + Docs: improve documentation of + name + , + description + and + uID + usage + + + Docs: add description of + parentUID + concept + + Docs: add description of symmetry inheritance + Docs: add description of engine nacelles + Docs: add description of mission definition + General improvements of the documentation + + + + + CPACS 3.3 + + Release in June 2021 + + + Revision of the mission definition including parameter lapses within segments ( + compatibility break + ) + + + Revision of the point performance definition ( + compatibility break + ) + + + Revision of performance requirements ( + compatibility break + ) + + + Revision of landing gears ( + compatibility break + ) + + + Revision of control surface tracks definition ( + compatibility break + ) + + + Load analysis: Revision of flightLoadCasesType ( + compatibility break + ) + + + Load analysis: Revision of aeroCasesType ( + compatibility break + ) + + + Load analysis: loadEnvelopesType relocated and envelope simplified to a single uID-Sequence ( + compatibility break + ) + + + Load analysis: Replaced dynamicAircraftModel elements by loadApplicationPointSets ( + compatibility break + ) + + + Flight dynamics: Group flightPerformance, flyingQualities and trim under flightDynamics parent node ( + compatibility break + ) + + Introduced a configuration node to describe aircraft and payload configurations + Fuselage profiles: Introduced rectangle and super ellipse as standard profiles + Fuselage profiles: Added vector to specify curve parameters for profiles with kinks + Internal structure: Added standard profiles to profile based structural elements + Internal structure: Added ribPosts element to wingRibCrossSectionType + Internal structure: Upper and lowerCap now optional in sparCellType + Internal structure: Stringers and frames can reference sections + MassBreakdown: Set mass inertia Jxy, Jxz and Jyz optional + MassBreakdown: Added mMiscellaneous element + MassBreakdown: Added fuselage walls + Added flight envelope to aircraft global element + Added new base types: doubleVectorBaseType, posIntVectorBaseType, doubleArrayBaseType + Added 'none' and 'inherit' to list of symmetry flags + Set mapType attribute of vector and array elements to optional (requires TiXI>=3.1) + + AeroMaps: Defined angleOfSideslip as input and added distinction between minimum and maximum angleOfAttack in aeroLimitMaps ( + compatibility break + ) + + + AeroMaps: Added missing singular incrementMap element to incrementMaps in aeroLimitsMap ( + compatibility break + ) + + + AeroMaps: Adopted the camelCase style for damping derivatives ( + compatibility break + ) + + + Introduced common nomenclature for speeds and altitudes ( + compatibility break + ) + + Control distributors are set to optional + Added instructions for superposition of control surface deflections + Further elaboration of development standards + General improvements of the documentation + + + + + CPACS 3.2 + + Release in February 2020 + + Replaced tool-specific elements with xsd:any element and strict schema request for validation + UIDs adapted to type xsd:ID and xsd:IDREF + UIDs optional for transformationType and pointTypes + Replaced xsd:sequence elements with xsd:all elements where possible + CpacsVersion element set to optional + GuideCurves are now optional for nacelleCowlType + Documentation adaptions + + + + + CPACS 3.1 + + Release in August 2019 + + Redefinition of aeroPerformanceMaps + Added nodes for detailed engine pylons and nacelles + Added nodes to model generic walls + Extension of material definition + Added fuselage compartment definition + Added fuselage fuel tank definition + Explicit wing stringer definition integrated into wing stringer definition + RelativeDeflections renamed to control parameters + Control distributors modified to only have a single command input vector + "cpacsVersion" restricted to current schema version + Code cleanup + Cpacs_schema.xml removed + Documentation adaptions + + + + + CPACS 3.0 + + Release in Jul 2018 + + New component segment definition; this is affecting all structural components of wings + Renamed angleOfYaw into angleOfSideslip + Fixes in documentation + Made all uID attributes required + Minor fixes in choices and typos + Added nodes for the geometry of generic system components + Added performance requirements for aircraft models + Redefined the whole mission definition including point performances + Made link to missionUID in trajectory optional + Added new parameters to enginePerformanceMap + Relocated mFixedLeadingEdge and mFixedTrailingEdge within the massBReakdown structure + Changed aeroPerformanceMap to use altitude and standard atmosphere instead of reynolds number + Added an optional local direction for guide curves and an illustration image + Announced toolspecifics definitions as deprecated; will be removed from CPACS in next release and should be managed in separate namespace by tool maintainers + Added an option for aerodynamic performance maps of elastic aircraft + Enabled the definition of multiple aeroPerformanceMaps + Enabled the use of spar points for rib placement and rib points for spar placement + Added explicit stringer definitions for wing cells + All issues for this release can be found online + https://github.com/DLR-LY/CPACS/issues + + + + + CPACS 2.3.1 + + Release in Jul 2016 + + CPACS 2.3.1 is a beta release, all parameters may be subject to change. + Added a branch for the definition of design studies. + Added thermal properties for materials. + Revised the definition of flights/flightplans. + Added an airline definition. + Added structure for skid gear components. + Changed the units for material density to SI units. + Revised the top level fleets node and put it into the new airline node. + All issues for this release can be found online + https://github.com/DLR-LY/CPACS/issues + + + + + CPACS 2.3 + + Release in Nov 2015 + CPACS 2.3 is the fourth public release of CPACS. Major changes include: + + Included vector notation for weight and balance. + Included flight system and flight dynamic information. + Included top level aircraft requirements. + Included a prototype for detailed nacelle geometries. + Included structural mounts. + Extended aero data set for loads. + Extended the mass breakdown. + Updated the symmetry definition, please take a look at the documentation point 5 and 6. + All issues for this release can be found online + https://github.com/DLR-LY/CPACS/issues + + + + + CPACS 2.2.1 + + Release in Feb 2015 + + CPACS 2.2.1 is a beta release, all parameters may be subject to change. + Included preliminary definition of guidecurves. + Included additional means to describe the wing structure. + Included preliminary fuselage fuel tanks. + Included preliminary load envelope. + Included preliminary flight performance and flight qualities. (flight dynamics will follow) + Updated toolspecifics + Updated uncertainty definition + all issues can be found online + http://code.google.com/p/cpacs/issues/list + + + + + CPACS 2.2 + + Release in May 2014 + + CPACS 2.2 is the third public release of CPACS. Major changes include + Additions and changes to the loadCaseType. + Included additional genericGeometricEntities for bellyfairings etc. + The mass breakdown is extended for a more detailed fuselage structure. + Steadiness information on the geometry is excluded from CPACS 2.2. CPACS 2.3 will include optional guidelines for smoother surfaces. + Uncertainties can now be specified (CPACS 2.2alpha doubleBaseType, CPACS 2.2 also in vector notations) + all issues can be found online + http://code.google.com/p/cpacs/issues/list + + + + + CPACS 2.1 + + Release in May 2013 + + CPACS 2.1 is the second public release of CPACS. Most of the implementation was already included in CPACS 2.01 + included fuselage structure and cabin definition + all data is defined according to the CPACS coordinate system. That is the initial coordinate system in which geometries are defined. Therefore, it can but must not meet your body axis. + the mass breakdown is extended for a more detailed wing structure + profiles can now be included based on a two-dimensional class shape transformation. The old parametrization will still be available. TIGL will learn CST asap. + all issues can be found online + http://code.google.com/p/cpacs/issues/list + + + + + CPACS 2.01 + + Release in Nov 2012 + + CPACS 2.01 is an internal release for the VAMP project. It is the testbed for CPACS 2.1 + included fuselage structure + additions to the load case definition + all issues can be found online + http://code.google.com/p/cpacs/issues/list + + + + + CPACS 2.0 + + Release in Mar 2012 + + CPACS 2.0 is the first public release + large impacts on the documentation + all issues can be found online + http://code.google.com/p/cpacs/issues/list + compatible with TIGL 2.0 + excluded fuselage structure, reintegration in CPACS 2.1 + + + + + CPACS 1.6 + + Release in Jul 2011 + + Thanks for the input on the documentation to Felix Dorbath, Till Pfeiffer, Alexander Koch, Falk Heinecke and Tom Otten + preliminary added enginePylons + deleted seatAssemblyPositionType + updated toolspecific blocks from handbook aero and cpacs mass updater + added weight and balance definition + added loads reference axis and dynamic aircraft model + added wing documentation + added weights documentation + added fleet documentation + added paramam toolspecific documentation + added wing tank definition + changed some names in the massBreakdown + deleted old loadCaseDefinitions + no more plural element for loadAnalyses + shifted groundforces to groundloadcases, this will need an update + added noseLandingGear + mainLandingGear can now have plural SideStruts + + + + + CPACS 1.5 + + Release in Feb 2011 + + uID for transformation + extended stringUIDBaseType with optional attribute isLink + all elements xxxUID are now of Type stringUIDBaseType + added new material definition from FA to distinguish between different material types + changed fuselage structure definition due to input from BK + changed rib definition in cells in component segments + cleaned up material definition in component segments + added cpacsVersion information to the header and updates types + added area and length to the loadCase reference on wing strips + added wingFuselageAttachment + + + + + CPACS 1.4 + + Release in Nov 2010 + + Geometry definition for engine and nacelle added + Trailing Edge Devices, Leading Edge Devices and Spoilers added + Rotorcraft added, similar to aircraft + Splitted up multiple Point Types + sparCell added uID + new inline Documentation introduced in CPACS type + + + + + CPACS 1.3 + + Release in Aug 2010 + + Fuel definition added + Introduced component segments for the wing structure + Mission definition was updated + VSAero toolspecific data updated + + + + + CPACS 1.2 + + Release in May 2010 + + Fuselage Structure Elements are updated following the input from BK + + stringers>arbitrary additional parameters: yBezugAtStartX, zBezugAtStartX, yBezugAtEndX, zBezugAtEndX + paxCrossBeams additional parameters: startX, endX + cargoCrossBeams additional parameters: startX, endX + paxCrossBeamStruts additional parameters: startX, endX + cargoCrossBeamStruts additional parameters: startX, endX + structure>pressureBulkhead: positionX instead of positionZ + reinforcementNumberVertical: number of vertical reinforcements + reinforcementNumberHorizontal: number of horizontal reinforcements + maxFlectionDepth: max camber of pressure bulkhead + reinforcementNumber: number of reinforcements rear pressure bulkhead + sheetProperties: definition of sheet properties + innerRadius: inner radius of the pressure bulkhead + + Dummy Wingbox element is included. This definition needs further enhancements + + cpacs>vehicles>aircraft>model>fuselage>fuselage>structure + Wingbox: + xStart: start of the wingbox area + xEnd: end of the wingbox area + zStart: upper limit of the wingbox area + + Damping Derivatives are added in the form of dcfxdp, dcfxdq, dcfxdr, dcfydp, etc. The data will be stored in the model/global/aeroperformaneMap under a new dampingDerivatives element. Unit is deg/sec. + StructureProfiles are defined in the profiles element. They are referenced in structuralElements for several entities such as stringer, frame etc. Currently they are referenced via 'structuralProfileUID' for name consistency it should be either only 'structure' or only 'structural' + Control Commands. The chain between pilot inputs and controlsurface deflections is now closed. + + Parameters located at cpacs\vehicles\aircraft\model\systems + cockpitControl: links from pilotInput to commandCase + commandCase: links from commandCase to controlDistributor or controlFunction + controlDistributor links to the controlSurface + controlLaws includes controlModes automatic and manual + controlModes contain controlFunctions + + TraFuMo toolspecific data added + + + + + CPACS 1.1 + + Release in Feb 2010 + + Fleets model added. The fleets modeling from CATS is introduced to CPACS 1.1 + Reference changed. The reference type in wingSegmentStripCoefficientsType was changed from referenceType to pointType + + + + + + + + + + + + + + + + + + + + + + + + + Actuator attachment + + + + + + + + + + + + + Relative spanwise position of the actuator. + Eta refers to the dimensions of the control surface. + + + + + + + + + + + + + + + + Definition of the position and material properties of + the control surface actuator attachment. + + + + Definition of the position and material properties of + the control surface actuator attachment. + Please refer to the picture below for the definition + of the parameters: + + + + + + + + + + + + + + Definition of the relative chordwise position + of the parent actuator attachment. Xsi refers to the parents + dimensions. + + + + + Definition of the relative height position of + the parent actuator attachment. relHeight refers to the parents + dimensions. + + + + + Definition of the material properties of the + actuator attachment at the parent. + + + + + + + + + + + + + actuatorFuselageWingAttachmentType + + + + + + + + + + + + + + + + + + + + + + + actuatorFuselageWingType + + + + + + + + + + + + + Reference to the actuator. + + + + + Definition of the actuator to fuselage + attachment. + + + + + Definition of the actuator to wing attachment. + + + + + + + + + + + + + + + Definition of the position and material properties of + the parent actuator attachment. + + + + Definition of the position and material properties of + the parent actuator attachment. + Please refer to the picture below for the definition + of the parameters: + + + + + + + + + + + + + + Definition of the relative chordwise position + of the parent actuator attachment. Xsi refers to the parents + dimensions. + + + + + Definition of the relative height position of + the parent actuator attachment. relHeight refers to the parents + dimensions. + + + + + Definition of the material properties of the + actuator attachment at the parent. + + + + + + + + + + + + + actuatorsFuselageWingType + + + + + + + + + + + + + Definition of one actuator (e.g. trim actuator + of an HTP) of the attachment. + + + + + + + + + + + + + Aerodynamic loads + + + + Description of the aerodynamic loads + + + + + + + + + + + + Angle of attack [deg] + + + + + + + Angle of sideslip [deg] + + + + + + + + + + + + + + + + Aerodynamic coefficients + + + + A set of aerodynamic coefficients in the aerodynamic coordinate system + + + + + + + + + + + + Drag coefficient in aerodynamic + coordinates + + + + + + + Coefficient of the side force vector in + aerodynamic coordinates (perpendicular + to lift and drag) + + + + + + + Lift coefficient in aerodynamic + coordinates + + + + + + + Aerodynamic moment around d-axis of the aerodynamic coordinate system + + + + + + + Aerodynamic moment around s-axis of the aerodynamic coordinate system + + + + + + + Aerodynamic moment around l-axis of the aerodynamic coordinate system + + + + + + + + + + + + + + + Specification + + + + Specification of the vehicle properties and dynamics + + + + + + + + + + + Altitude + + + + + + + Mach number + + + + + + + Angle of sideslip [deg] + + + + + + + + Angle of attack [deg] + + + + + + + Target lift coefficient + + + + + + + + Normalized roll rate [rad/sec]. It is specified around the global x-axis + with the aircraft model's global reference point as origin and + nondimensionalized by: pStar = p * reference length / flow speed. + + + + + + + Normalized pitch rate [rad/sec]. It is specified around the global y-axis + with the aircraft model's global reference point as origin and + nondimensionalized by: qStar = q * reference length / flow speed. + + + + + + + Normalized yaw rate [rad/sec]. It is specified around the global z-axis + with the aircraft model's global reference point as origin and + nondimensionalized by: rStar = r * reference length / flow speed. + + + + + + + + Reference to a weight and balance description + + + + + + + + + + + + Aerodynamic load cases + + + + Combines a set of aerodynamic load cases + + + + + + + + + + + + + + + + + + + + Aerodynamic load case + + + + Specification of an aerodynamic load case + + + + + + + + + + + + Name + + + + + + + Description + + + + + + + + + + + + + + + + + Aerodynamic loads of components + + + + Specification of the aerodynamic loads of components + + + + + + + + + + + + + + + + + + + + Aerodynamic data of components + + + + Aerodynamic data of individual components of the aircraft (e.g. control surface loads and hinge moments) + + + + + + + + + + + + Reference to a component uID + + + + + + + + + + + + + + + Aerodynamic loads of the vehicle + + + + Description of the aerodynamic loads of the vehicle + + + + + + + + + + + + + + + + + + + + + aeroelasticDivergenceType + + + AeroelasticDivergence type, containing the results from + aeroelastic analysis + + + + + + + + + + + + + + + + + + + aeroelasticStaticMaxDisplacementType + + + AeroelasticStaticMaxDisplacement type, containing the + Maximum static displacement from aeroelastic analysis + + + + + + + + + + Maximum translation + + + + + Maximum rotation + + + + + + + + + + + + + Aeroelasticity + + + Aeroelastics type, containing the results from + aeroelastic analysis + + + + + + + + + + + + + + + + + + + + Increment maps for limitation values due to movable device deflections + + + Specification of aerodynamic coefficient increments due to movable device deflections (e.g., control + surfaces or landing gears). + + + + + + + + + + + + + + + + + + + Increment maps for limitation values due to movable device deflections + + + Specification of aerodynamic coefficient increments due to movable device deflections (e.g., control + surfaces or landing gears). + + + + + + + + + + + Configuration uID + + + + + Reference to an increment map of the aeroPerformanceMap + + + + + + Increments of the vehicle operation limits + + + + + + + + + + + + + + Aerodynamic limitations + + + + + This map explicitly specifies limitations of a vehicle in terms of angles of attack and sideslip angles. + All vectors, i.e. + altitude + , + machNumber + , + angleOfSideslip + and + angleOfAttack + , must have the + same length. To avoid redundancy with the + aeroPerformanceMap + , this type does not contain + any aerodynamic coefficients. + + + Since + angleOfSideslip + and + angleOfAttack + are closely interdependent for a given + machNumber + and + altitude + combination, a positive and negative maximum + angleOfAttack + is defined for a given combination of + machNumber + , + altitude + and + angleOfSideslip + . The limits of + angleOfSideslip + can be determined by evaluating the nominal decrease of + angleOfAttack + values or by + agreeint with the data supplier that the minimum and maximum value of the + angleOfSideslip + vector corresponds with physical limits. + + In order to avoid data redundancy, the operational limits should not reflect the extrema of aerodynamic + coefficients as these can be extracted from the performanceMap via interpolation. + + Note: + In future CPACS versions, a revision of the + aeroLimitsMap + will be targeted, since operational limits are not a purely aerodynamic issue. + + + + + + + + + + + + + Altitude [m] + + + + + + + Mach number + + + + + + + Angle of sideslip + + + + + + + + + + + + + + + + Vehicle operation limit + + + + Vehicle operation limit defined by sets of minimum and maximum + angleOfSideslip + and minimum and maximum + angleOfAttack + for a given altitude and Mach number. + This might be, e.g., a safety margin to the angle of attack at maximum lift or the flight + attitude a fighter aircraft is capable to fly in stalled conditions. The corresponding aerodynamic coefficients must + be extracted from the aeroPerformanceMap. + + + + + + + + + + + Minimum angle of attack defining the operation limit. Must be a vector of the same length as angleOfSideslip, machNumber and altitude. [deg] + + + + + Maximum angle of attack defining the operation limit. Must be a vector of the same length as angleOfSideslip, machNumber and altitude. [deg] + + + + + + + + + + + + + Aerodynamic map + + + + + The aeroMap contains aerodynamic coefficients and derivatives for a specific set of aerodynamic + and configurative boundary conditions. + + + The + aeroMap + allows for the simultaneous specification of multiple + controlDevice + settings. + In this case, it is assumed that a cumulative setting is built by summing up the individual settings. The correct + sequence of this summation is described in the + controlDistributorType + documentation. + + + + + + + + + + + + Name + + + + + Description + + + + + + + + + + + + + + + + + Boundary conditions + + + Specification of boundary conditions. + + + + + + + + + + + + Offset from temperature of the + atmospheric model [K]. For more details + on atmospheric models, please refer to + documentation of the <CPACS> root + element. + + + + + + + Configuration settings + + + + + + + + + + + + + + Increment maps for aerodynamic coefficients + + + + + + + + + + + + + + + + + + + Increment map from aerodynamic coefficients + + + The increment map is composed of two-dimensional arrays. The first dimension is given by the + length of the input vectors of the baseline aeroPerformanceMap and the second dimension by the vector of relative + deflections (or command inputs) of control surfaces (or control distributors). An example is described in the <CPACS> + root element. + + + + + + + + + + + + Reference to the uID of a control device, e.g. a control surface or a landing gear + + + + + Value of the command parameters of a control distributor. If not given explicitly in the control distributor, linear interpolation between the neighboring points is required. + + + + + + + Reference to a control distributor uID + + + + + Command inputs of a control distributor given as vector. If not given explicitly in the control distributor, linear interpolation between the neighboring points is required. + + + + + + + Increment of drag coefficient in aerodynamic coordinates + + + + + Increment of coefficient of the side force vector in aerodynamic coordinates (perpendicular to lift and drag) + + + + + Increment of lift coefficient in aerodynamic coordinates + + + + + Increment of cmd + + + + + Increment of cms + + + + + Increment of cml + + + + + + + + + + + + + + aeroPerformanceMapRCType + + + AeroPerformanceMapRC type, containing a performance map + with aerodynamic data. Array order is: angleOfAttack min->max + then angleOfSideslip then altitude then machNumber + + + + + + + + + + Atmospheric model and temperature offset + + + + + Mach number + + + + + Altitude + + + + + Sideslip angle + + + + + Angle of attack + + + + + Name and version of the tool used to compute + the aerodynamic performance + + + + + Modeling level of the methods used to compute + the aerodynamic performance. The higher the analysisLevel, the + higher the quality of the results. Possible use of + analysisLevel: 0- 9 = Statistical models, 10-19 = Analytic + models, 20-29 = Lifting line method, 30-39 = Panel method, 40-49 + = Panel-BL-coupled method, 50-59 = Full potential method, 60-69 + = Full potential-BL coupled method, 70-79 = CFD euler method, + 80-89 = CFD euler-bl coupled method, 99-99 = CFD RANS method, + >=100 = Experimental data. + + + + + + + + + + + + + + + + + + + + aeroPerformanceMapsRCType + + + aeroPerformanceMapsRC type, containing multiple + aeroPerformanceMapRC nodes for different cases + + + + + + + + + + + + + + + + + + + Aerodynamic coefficients and derivatives + + + + + Description + + + The aeroPerformanceMap contains a map + with aerodynamic data of the complete aircraft in the form of + nondimensional coefficients. The force coefficients in + i + -direction ( + ci + ) + are nondimensionalized by dynamic pressure and reference area, + the moment coefficients ( + cmi + ) by dynamic pressure, reference + area and reference length. + + All coefficients in the aeroPerformanceMap relate to + the aerodynamic coordinate system which is deducted from the CPACS coordinate system by + the transformations of angle of attack and angle of yaw. See the documentation of the + CPACS element for further details. + + + The dependent parameters of the aeroPerformanceMap are + altitude + , + machNumber + , + angleOfSideslip + and + angleOfAttack + . These elements are vectors of equal length, where values + with identical indices belong together. The solution vectors + ci + and + cmi + have the same length as the input vectors. Shown below is an example where + with 10 values per vector: + + <altitude mapType="vector">12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02;12e+02</altitude> +<machNumber mapType="vector">0.2;0.2;0.2;0.2;0.2;0.2;0.2;0.2;0.2;0.2</machNumber> +<angleOfSideslip mapType="vector">0;0;0;0;0;2;2;2;2;2</angleOfSideslip> +<angleOfAttack mapType="vector">-2;0;2;4;6;-2;0;2;4;6</angleOfAttack> +<cd mapType="vector">0.056;0.094;0.132;0.17;0.208;0.072;0.11;0.148;0.186;0.224</cd> +<cs mapType="vector">0.;0.;0.;0.;0.;0.01;0.015;0.02;0.025;0.03</cs> +<cl mapType="vector">-0.1;0.04;0.18;0.32;0.46;-0.08;0.03;0.14;0.25;0.36</cl> + + + The aerodynamic coefficients for + altitude + =1200m, + machNumber + =0.2, + angleOfSideslip + =0° and + angleOfAttack + =6° can be found at the 5th index: + cd + =0.208, + cs + =0 and + cl + =0.46. + + + + + + + + + + + + + + + Altitude [m] + + + + + + + Mach number + + + + + + + Sideslip angle [deg] + + + + + + + Angle of attack [deg] + + + + + + + Drag coefficient in aerodynamic + coordinates + + + + + + + Coefficient of the side force vector in + aerodynamic coordinates (perpendicular + to lift and drag) + + + + + + + Lift coefficient in aerodynamic + coordinates + + + + + + + + + + + + + + + + + + + aeroPerformanceType + + + aeroPerformance type, containing performance maps with + aerodynamic data of an airfoil. + + + + + + + + + + Aerodynamic performance map of the full + configuration + + + + + Aerodynamic performance maps of isolated + fuselages + + + + + Aerodynamic performance maps of isolated wings + + + + + + Aerodynamic performance maps of control + surfaces + + + + + Aerodynamic performance maps of isolated + airfoils + + + + + + + + + + + + + Aerodynamic performance + + + + The aerodynamic coefficients and derivatives are stored in aerodynamic maps. Individual maps can be used to + gather the aerodynamic characteristics for specific boundary conditions. + + + + + + + + + + + + + + + + + + + + Global analysis information + + + + + + + + + + + + + + + + + + + + + + Results from several analysis + modules connected to CPACS + + + AircraftAnalyses type, containing detailed analysis + data of the aircraft + Within this element results from analysis modules are + stored that rely to the overall definition of the aircraft. These + include e.g. aerodynamic data or loadCases + For further documentation please refer to the + respective elements. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Control elements + + + Specification of control element settings. Control elements can be controlDistributors + or individual control devices, such as control surfaces or landing gears. + + + + + + + + + + + + + + + + + + + Control element + + + Specification of an control element setting. A control element can be a controlDistributor + or an individual control device, such as a control surface or a landing gear. + + + + + + + + + + + Reference to the uID of a control device, e.g. a control surface or a landing gear + + + + + Control parameter of the control device + + + + + + + Reference to a control distributor uID + + + + + Value of the command parameter of a control distributor. If not given explicitly in the control distributor, linear interpolation between the neighboring points is required. + + + + + + + + + + + + + + Global data + + + AircraftGlobal type, containing global data of the + aircraft + + + + + + + + + + + designRange equals the full payload max + range, i.e. point B in payload range + diagram + + + + + + + + + + + + + + + + + + Aircraft model + + + + + The + aircraftModelType + contains the geometric aircraft + model and associated data. + + + Elements specifying the geometry of the aircraft are + fuselages + , + wings + , + engines + (referenced via + uID + ), + enginePylons + , + landingGear + , + systems + (to some extend) and + genericGeometryComponents + . + + + Other elements are dedicated to additional data associated to this aircraft model. Brief and concise analysis results are stored + in the + global + node. The + analysis + node contains + extensive results from multidisciplinary analysis modules. + + + In the current CPACS version requirements only refer to the aircraft performance and are therefore specified in the + performanceRequirements + node. + + + + + + + + + + + + Name of the aircraft model + + + + + + Description of the aircraft model + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Aircraft + + + + + The + aircraftType + contains a list of aircraft models. + + + Note: Since there is no distinction between plural and singular in English, + aircraft + refers to plural form, while a single aircraft itself is referenced as + model + . + + + + + + + + + + + + + + + + + + + + + airfoilAeroPerformanceType + + + airfoilAeroPerformance type, containing performance maps + with aerodynamic data of an airfoil. + + + + + + + + + + Reference to the uID of the analysed airfoil + + + + + + References used for the calculation of the + force and moment coefficients of the airfoil (in the airfoil + axis system!) + + + + + Calculated aerodynamic performance maps of the + airfoil + + + + + + + + + + + + + airfoilsAeroPerformanceType + + + airfoilsAeroPerformance type, containing + airfoilsAeroPerformance + + + + + + + + + + + + + + + + + + + airframeMaintenanceCostType + + + + + + + + + + + + + + + + + + + + + + + Airlines + + + Contains a list of different airlines + + + + + + + + + + + + + + + + + + + airlineType + + + Describes a specific airline and their fleet + + + + + + + + + + Name of the airline + + + + + Description of the airline + + + + + + + + + + + + + + + Airport compatibility + + + + + + + + + + + + + + + + + + + + + + + + + + Airports + + + Airports type, containing data of the airports + + + + + + + + + + + + + + + + + + + + airportType + + + Airport type, containing data of an airport + + + + + + + + + + Name of airport + + + + + Description of airport + + + + + IATA 3-letter-code + + + + + ICAO 4-letter-code + + + + + Position in degrees north + + + + + Position in degrees east + + + + + Airport elevation + + + + + + + + + + + + + + + alignmentCrossBeamType + + + + + + + + + + + + + Offset in direction of extrusion, first side + (absolute value) + + + + + Offset in direction of extrusion, second side + (absolute value) + + + + + Rotation around local x axis (extrusion axis) + + + + + + Translation along local y axis (perpendicular + to extrusion axis) + + + + + Translation along local z axis (perpendicular + to x ynd y axes) + + + + + + + + + + + + + + alignmentFloorPanelType + + + + + + + + + + + + + Offset from seat rail 1 reference Position in + local y direction (in plane of panel, absolute value) + + + + + + Offset from seat rail 2 reference position in + local y direction (in plane of panel, absolute value) + + + + + + Offset from seat rail 1 reference position in + local z direction (in plane of panel, absolute value)) + + + + + + + + + + + + + + + alignmentStringFrameType + + + + + + + + + + + + + Rotation around local x axis (extrusion axis) + + + + + + Translation along local y axis (perpendicular + to extrusion axis) + + + + + Translation along local z axis (perpendicular + to x ynd y axes) + + + + + + + + + + + + + + alignmentStructMemberType + + + + + + + + + + + + + Offset in direction of extrusion (absolute + value) + + + + + Rotation around local x axis (extrusion axis) + + + + + + Translation along local y axis (perpendicular + to extrusion axis) + + + + + Translation along local z axis (perpendicular + to x ynd y axes) + + + + + + + + + + + + + + Alternating current + + + + + + + + + + + Effective voltage (also peak voltage) [V] + + + + + + + Frequency [Hz] + + + + + + + Frequency [Rad] + + + + + + + + + + + + + + Alternating current + + + + + + + + + + + Effective voltage (also peak voltage) [V] + + + + + + + Frequency [Hz] + + + + + + + Frequency [Rad] + + + + + + + + + + + + + + + Anisotropic material properties for 2D materials + + + + + Defines the material properties for a linear anisotropic material in the plane stress state (i.e., shell). The stress-strain relationship is defined as: + + + + The terminology of this complex type refers to the following literature: + + [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. + [2] J. N. Reddy, Mechanics of Laminated Composite Plates and Shells: Theory and Analysis, Second Edition. CRC Press, 2004. + + + + + + + + + + + + Coefficient 11 of reduced stiffness matrix [N/m^2] + + + + + Coefficient 12 of reduced stiffness matrix [N/m^2] + + + + + Coefficient 13 of reduced stiffness matrix [N/m^2] + + + + + Coefficient 22 of reduced stiffness matrix [N/m^2] + + + + + Coefficient 23 of reduced stiffness matrix [N/m^2] + + + + + Coefficient 33 of reduced stiffness matrix [N/m^2] + + + + + Thermal expansion coefficient in material direction + 1 [1/K] + + + + + Thermal expansion coefficient in material direction + 2 [1/K] + + + + + Thermal expansion coefficient in material direction + 12 [1/K] + + + + + Thermal conductivity of the material in material direction 1 [W/(m*K)] + + + + + + Thermal conductivity of the material in material direction 2 [W/(m*K)] + + + + + + Thermal conductivity of the material in material direction 3 [W/(m*K)] + + + + + + Allowable stress for tension in material direction 1 [N/m^2] + + + + + + Allowable stress for compression in material direction 1 [N/m^2] + + + + + + Allowable stress for tension in material direction 2 [N/m^2] + + + + + + Allowable stress for compression in material direction 2 [N/m^2] + + + + + + Allowable stress for shear [N/m^2] + + + + + + Allowable strain for tension in material direction 1 + + + + + Allowable strain for compression in material direction 1 + + + + + + Allowable strain for tension in material direction 2 + + + + + Allowable strain for compression in material direction 2 + + + + + + Allowable strain for shear + + + + + + + + + + + + + + Anisotropic material properties for 3D materials + + + + + Defines the material properties for a linear anisotropic material in three spatial directions (i.e., solid). The stress-strain relationship is defined as: + + + + The terminology of this complex type refers to the following literature: + + [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. + [2] J. N. Reddy, Mechanics of Laminated Composite Plates and Shells: Theory and Analysis, Second Edition. CRC Press, 2004. + + + + + + + + + + + + Coefficient 11 of stiffness matrix [N/m^2] + + + + + Coefficient 12 of stiffness matrix [N/m^2] + + + + + Coefficient 13 of stiffness matrix [N/m^2] + + + + + Coefficient 14 of stiffness matrix [N/m^2] + + + + + Coefficient 15 of stiffness matrix [N/m^2] + + + + + Coefficient 16 of stiffness matrix [N/m^2] + + + + + Coefficient 22 of stiffness matrix [N/m^2] + + + + + Coefficient 23 of stiffness matrix [N/m^2] + + + + + Coefficient 24 of stiffness matrix [N/m^2] + + + + + Coefficient 25 of stiffness matrix [N/m^2] + + + + + Coefficient 26 of stiffness matrix [N/m^2] + + + + + Coefficient 33 of stiffness matrix [N/m^2] + + + + + Coefficient 34 of stiffness matrix [N/m^2] + + + + + Coefficient 35 of stiffness matrix [N/m^2] + + + + + Coefficient 36 of stiffness matrix [N/m^2]2] + + + + + Coefficient 44 of stiffness matrix [N/m^2]] + + + + + Coefficient 45 of stiffness matrix [N/m^2] + + + + + Coefficient 46 of stiffness matrix [N/m^2] + + + + + Coefficient 55 of stiffness matrix [N/m^2] + + + + + Coefficient 56 of stiffness matrix [N/m^2] + + + + + Coefficient 66 of stiffness matrix [N/m^2] + + + + + Thermal expansion coefficient in material direction + 1 [1/K] + + + + + Thermal expansion coefficient in material direction + 2 [1/K] + + + + + Thermal expansion coefficient in material direction + 3 [1/K] + + + + + Thermal expansion coefficient affecting strain in material direction + 23 [1/K] + + + + + Thermal expansion coefficient affecting strain in material direction + 31 [1/K] + + + + + Thermal expansion coefficient affecting strain in material direction + 12 [1/K] + + + + + Thermal conductivity of the material in material direction 1 [W/(m*K)] + + + + + + Thermal conductivity of the material in material direction 2 [W/(m*K)] + + + + + + Thermal conductivity of the material in material direction 3 [W/(m*K)] + + + + + + Thermal conductivity of the material which couples heat flux in material direction 2 with temperature gradient in material direction 3 [W/(m*K)] + + + + + + Thermal conductivity of the material which couples heat flux in material direction 3 with temperature gradient in material direction 1 [W/(m*K)] + + + + + + Thermal conductivity of the material which couples heat flux in material direction 1 with temperature gradient in material direction 2 [W/(m*K)] + + + + + + Allowable stress for tension in material direction 1 + [N/m^2] + + + + + Allowable stress for compression in material + direction 1 [N/m^2] + + + + + Allowable stress for tension in material direction 2 + [N/m^2] + + + + + Allowable stress for compression in material + direction 2 [N/m^2] + + + + + Allowable stress for tension in material direction 3 + [N/m^2] + + + + + Allowable stress for compression in material + direction 3 [N/m^2] + + + + + Allowable stress for shear in 2-3 plane [N/m^2] + + + + + Allowable stress for shear in 3-1 plane [N/m^2] + + + + + + Allowable stress for shear in 1-2 plane [N/m^2] + + + + + Allowable strain for tension in material direction 1 + + + + + + Allowable strain for compression in material + direction 1 + + + + + Allowable strain for tension in material direction 2 + + + + + + Allowable strain for compression in material + direction 2 + + + + + Allowable strain for tension in material direction 3 + + + + + + Allowable strain for compression in material + direction 3 + + + + + Allowable strain for shear in 2-3 plane + + + + + + Allowable strain for shear in 3-1 plane + + + + + + Allowable strain for shear in 1-2 plane + + + + + + + + + + + + + + Category (ATA chapters) + + + + + + + + Environmental control + + + + + Auto flight + + + + + Communications + + + + + Electrical power + + + + + Equipment/furnishings + + + + + Fire protection + + + + + Flight controls + + + + + Fuel + + + + + Hydraulic power + + + + + Ice and rain protection + + + + + Landing gear + + + + + Lights + + + + + Water/waste + + + + + Cabin system + + + + + Cargo and accessory compartment + + + + + + + + + + + atmosphericModelType + + + Defines the the athmospheric model which should be used. + Currently there is only a single option which is ISA for ICAO Standard + atmosphere (ISA) from 1993. For more details on atmospheric + models, please refer to documentation of the <CPACS> root + element. + + + + + + + + + + Atmospheric model (e.g. ISA for ICAO Standard + atmosphere (ISA) from 1993). + + + + + + + + + + + + Offset from temperature of the atmospheric model [K]. + For more details on atmospheric models, please refer to documentation + of the <CPACS> root element. + + + + + + + + + + + + + Atmospheric model + + + Available options: ISA. See documentation of <CPACS> root element for further details. + + + + + + + + + + + + + + + + + + Definition of attachment pins for the wing-fuselage + attachment. + + + Definition of attachment pins for the wing-fuselage + attachment. + + + + + + + + + + + + + + + + + + + Attachment pin of the wing-fuselage-attachment. + + + + Attachment pin of the wing-fuselage-attachment. + + + + + + + + + + + + + Definition which translation degrees of + freedom are blocked. Default x=0 (free); y=1 (blocked); z=1 + (blocked). + + + + + + + + + + + + + + + + Bogie axle assemblies + + + + A list of axles that are attached to the bogie + and their relative position to it + + + + + + + + + + + + + + + + + + + + Bogie axle assembly + + + Description of an axle installed on the bogie and its + relative position to it + + + + + + + + + + + Relative position of the axle to the bogie (if more than one axle is defined; 0 = forward end of bogie; 1 = rear end of bogie) + + + + + + + + + + + + + + + + + + + Axle + + + Geometric description and material properties of the + landing gear axle + + + + + + + + + + Length of the axle. For a single wheel, the length is equal to the distance between the center of the piston and the center of the wheel. For two wheels, the length is equal to the distance between the centers of the wheels with the axis being centered w.r.t. to the Piston. + + + + + Axle shaft properties + + + + + Number of wheels attached to this axle + + + + + Defines the side of the first wheel (inboard or outboard; inboard corresponds to the negative y-direction or in flight direction left) for odd number of wheels on this axis. Each additional wheel is the added on the opposite site of the previous wheel. + + + + + + + + + + + + Properties of the wheel(s) attached to this axle. If more than one wheel is attached, all wheels on a single axis have the same properties. + + + + + + + + + + + + + + Batteries + + + + + + + + + + + + + + + + + + + Battery + + + + + + + + + + UID of an electric energy carrier + + + + + + + + + + + + + beamCrossSectionType + + + beamCrossSectionType, containing the beam geometrical + properties + + + + + + + + + + + + + + + + + + + + + + + + beamStiffnessType + + + globalBeamStiffnessType, containing the beam + stiffnesses such as EA, EI + + + + + + + + + + + + + + + + + + + + + + + + + + blockedDOFType + + + + + + + + + + + + + + + + + + + + + + + Bogie + + + Geometric description and material properties of the + landing gear axle bogie (including the axle configuration) + + + + + + + + + + Length of the bogie + + + + + Tilt angle of the bogie in airborne conditions + + + + + + + + + + + + + + + + booleanBaseType + + + Base type for boolean nodes (including external data + attributes) + + + + + + + + + + + + + + + + + + + Bounding Box + + + + + + + + + + Length in x + + + + + Length in y + + + + + Length in z + + + + + Origin + + + + + + + + + + + A list of uIDs referencing other structural/geometric + elements that shall serve as a boundary of the wall + element. Possible references are floor, wall or + genericGeometryComponent. A major requirement is that + the referenced element has an intersection with the wall + for at least the distance between two wall positions. So + that a full geometric face of the wall is bounded by it. + Neighbouring wall faces that are not completely bounded + by the reference element are not affected. + + + + + + + + + UID referencing another + structural/geometric element that shall + serve as a boundary of the wall element. + Possible references are floor, wall or + genericGeometryComponent. + + + + + + + + + + + + + + System breakdown data + + + + + + + + + + + + + + + + + + + System breakdown data + + + + + + + + + + + + + + + + + + + Cabin aisles + + + + + + + + + + + + + + + + + + + + + + Aisle + + + Aisles has as many entries as there are aisles in the + cabin. In a normal single aisle there are two aisles: the cabin + aisle and the aisle leading to the cockpit. + + + + + + + + + + Name + + + + + Description + + + + + Longitudinal coordinates. The + number of coordinates can be chosen as appropriate, the minimum + number is two. The coordinates are relative to the cabin origin. + + + + + + Center points of the aisle. The + y-vector has to have same length as the x-vector. The aisle + stretches equally left and right of the provided y-coordinate. + + + + + + Width of the aisle at floor level at each + y-coordinate + + + + + + + + + + + + + + Cabin geometry contours + + + Cabin geometry contour line collection type. By providing more than one entry, + a 3D cabin space can be described. + + + + + + + + + + + + + + + + + + + + Cabin geometry contour + + + Type to define a lateral position value "y" at a given height "z" (in the parent deck coordinate system) + for each entry "x" in the parent cabin geometry definition. + + + + + + + + + + + Vector with y-coordinates + + + + + Height z + + + + + + + + + + + + + Geometry + + + + + [ + WARNING: + This type is known to be susceptible to + inconsistencies and might therefore be removed in a future version of CPACS] + + + The geometry of the cabin roughly corresponds to the available design space in the cabin. + It is given in terms of constant height contour lines. + The lines all share a common + x + -vector. + The + y + vector provides the lateral + contour at Z-coordinate provided by the constant value + z + . + One or more contour lines can be given. + The cabin geometry is assumed to be symmetric. + + + + + + + + + + + + + + + Name + + + + + Description + + + + + + Vector of x coordinates + + + + + + + + + + + + + Cabin spaces + + + + + + + + + + + + + + + + + + + + + + Space + + + spaces describe areas in the cabin that need to be + clear for use as emergency area. Depending on the type of area, + it can have a height limit. The spaces are required for + downstream cabin design, for example to describe an empty cabin. + + + + + + + + + + + Name + + + + + Description + + + + + Vector with x-coordinates. These describe an area, so they + are not monotonous ascending. + + + + + Vector with y-coordinates at given x-coordinates. Warning: + x-y do not represent a function as single x-positions can have + multiple y-coordinates. Hence, no interpolation is possible. + + + + + + Height above the floor that is required to + be empty of any objects + + + + + + + + + + + + + + Cap + + + + SparCap type, containing the cross section area of the + spar cap and the material properties. + Please find below a picture where all spar cross + section parameters as well as the orientation references for + the material definition can be found: + + + + + + + + + + + + + + Area of the cap + + + + + + + + + + + + + + + Cargo container elements + + + Cargo container element collection type + + + + + + + + + + + + + + + + + + + Cargo container element for use in the decks + + + + + + + + + + + + + + + + + Name + + + + + Description + + + + + + + + + + + + + + + + + + + + + + + + Cargo container geometry + + + + + + + + + + Contour: single or double + + + + + + + + + + + + + Delta x + + + + + + Delta y + + + + + + Delta y of the base + + + + + + Delta z + + + + + + Delta z kink + + + + + + + + + + + + + + Cargo containers + + + Cargo container instance collection type. + + + + + + + + + + + + + + + + + + + Cargo container + + + Cargo container type for placing an instance of a cargo container in the parent deck. + + + + + + + + + + Name + + + + + Description + + + + + UID of the cargo container element in the cpacs/vehicles/deckElements node + + + + + Position in x + + + + + Position in y + + + + + + + + + + + + + + cargoCrossBeamsAssemblyType + + + CargoCrossBeamsAssembly type, containing cargo + crossBeam assemblies + + + + + + + + + + + + + + + + + + + cargoCrossBeamStrutsAssemblyType + + + CargoCrossBeamStrutsAssembly type, containing cargo + crossBeam strut assemblies + + + + + + + + + + + + + + + + + + + cargoDoorsAssemblyType + + + CargoDoorsAssembly type, containing cargo door + assemblies + + + + + + + + + + + + + + + + + + + Ceiling panel + + + Ceiling panel element collection type + + + + + + + + + + Ceiling panel element for use in the decks + + + + + + + + + + + + + Ceiling panels + + + Ceiling panel instance collection type. + + + + + + + + + + Ceiling panel + + + + + + + + + + + + + + Chordwise positioning of wing cells. + + + CellPositioningChordwise defines the chordwise direction of a wing cell either in two xsi + (xsi1 at innerBorder and xsi2 at outerBorder) coordinates, via referencing a spar-uID or via a + contour coordinate in chordwise direction. + + + + + + + + + + + Relative chordwise position of the inner end. + + + + + Relative chordwise position of the outer end. + + + + + + Reference to a spar as chordwise border. + + + + + Chordwise contour coordinate as chordwise border. 0 equals LE, 1 equals TE. + + + + + + + + + + + + + Spanwise positioning of wing cells. + + + CellPositioningSpanwise defines the chordwise direction of a wing cell either in two eta + (eta1 at leadingEdge and eta2 at trailingEdge) coordinates, via referencing a rib-uID or via a contour + coordinate in chordwise direction. + + + + + + + + + + + Relative spanwise position of the forward end. + + + + + Relative spanwise position of the rear end. + + + + + + + RibNumber is the reference to the rib number of the rib set which is referenced by 'ribDefinitionUID'. + + + + + Reference to a ribDefinition set. The single rib of this ribDefinition set is defined by using 'ribNumber'. + + + + + + Spanwise contour coordinate as spanwise border. 0 equals root, 1 equals tip. + + + + + + + + + + + + + centerFuselageAreasAssemblyType + + + centerFuselageAreasAssembly type, containing center + fuselage area assembly + + + + + + + + + + + + + + + + + + + centerFuselageAssemblyType + + + CenterFuselageAssembly type, containing wing box + assemblies + + + + + + + + + Choice between different center fuselage + modelling options + + + + Simplified center fuselage definition (rigid + body) + + + + UID of first frame in rigid center fuselage + area + + + + + UID of last frame in rigid center fuselage + area + + + + + UID of start stringer to define center + fuselage area + + + + + UID of end stringer to define center fuselage + area + + + + + + Detailed low wing center fuselage definition + (draft definition) + + + + + + Detailed high wing center fuselage definition + (draft definition) + + + + + + + + + + + + + + + centerFuselageHighWingConfiguration + + + + + + + + + + + + + + + + + + + + + + centerFuselageKeelbeamType + + + CenterFuselage / Keelbeam definition between mainframe1 + und mainframe3 + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + centerFuselageLateralPanelsType + + + CenterFuselage / lateral Panel definition between + mainframe2 und mainframe3 + + + + + + + + + + + + + + + + + + + + + + + + + + centerFuselageLongFloorBeamConnectionType + + + CenterFuselage / Long. floor beam connection + + + + + + + + + + + + + + + + + + + + + centerFuselageLowWingConfiguration + + + + + + + + + + + + + + + + + + + + + + + + + centerFuselageMainFramesType + + + CenterFuselage / main frame definition, containing + mainframe and pressure Bulkhead definitions + + + + + + + + + + + + + + + + + + + + + + + + centerFuselagePressureFloorType + + + CenterFuselage / pressure floor definition between + mainframe2 und mainframe3 + + + + + + + + + + + + + + + + + + + + + + + + centerFuselagePressureFloorType + + + CenterFuselage / side box definition between mainframe2 + und mainframe3 + + + + + + + + + + + + + + + + + + + + + certificationCasesType + + + + + + + + + + + + + + + + + + + + + + Change log + + + + + + + + + + + + + + + + + + + chargesCostType + + + + + + + + + + + + + + + + + + + + + + + + + + Chemical energy carriers + + + + + + + + + + + + + + + + + + + Chemical energy carrier + + + + + + + + + + Name + + + + + Description + + + + + Type of energy carrier + + + + + + + + + + + + + Lower heating value + + + + + Density at 15deg C + + + + + CO2 emission index + + + + + H2O emission index + + + + + Energy specific cost + + + + + Freezing point + + + + + + + + + + + + + + Aerodynamic contributions of a chrordwise part within a wing segment strip + + + + Contains a list of chordwise parts within a wing segment strip for which aerodynamic coefficients are specified + + + + + + + + + + + + + + + + + + + + Aerodynamic contributions of a chordwise part within a within a wing segment strip + + + + + Describes the contributions of a specific par within a wing segment to the total aerodynamic coefficients of a wing segment strip + + + A + chordwisePart + aescribes the contributions of a specific chordwise part within a wing + strip + to the total aerodynamic coefficients of this + strip + . It extends spatially between the two + eta + positions of the parent + strip + (see + strip + documentation) and four + xsi + positions in the segment coordinate system. + As with the parent stips, only the trailing border ( + ..ToSegmentXsi + ) of a + chordwisePart + is defined, while the leading border always equals the trailing border of the preceding + chordwisePart + (or + 0 + for the first part). + To account for oblique trailing borders (e.g., to match the aileron on a tapered wing) two different + toSegmentXsi + positions can be defined, one at the inner border ( + innerBorderToSegmentXsi + ) and one at the outer border ( + innerBorderToSegmentXsi + ) of the parent strip. + The + innerBorderToSegmentXsi + and + outerBorderToSegmentXsi + of the last + chordwisePart + must be equal to 1. + + + + + + + + + + + + + Chordwise coordinate xsi in the segment coordinate system to define the end position of the chordwisePart at the inner eta border + + + + + + + Chordwise coordinate xsi in the segment coordinate system to define the end position of the chordwisePart at the outer eta border + + + + + + + + + + + + + + + + Class divider + + + Class divider element collection type + + + + + + + + + + Class divider element for use in the decks + + + + + + + + + + + + + Class dividers + + + Class divider instance collection type. + + + + + + + + + + Class divider + + + + + + + + + + + + + + cockpitControlsType + + + Cockpit controls type, containing the cockpit controls + + Some controls are mandatory, others can be added via + cockpitControl elements + + + + + + + + + + + + + + + + + + + + + + cockpitControlType + + + single cockpitControl is defined by a pilotInput and a + commandOutput. The commandOutput is linked to the commandCase + + + + + + + + + + + + + + + + + + + + + + + + + Reference values for aerodynamic coefficients + + + + Specification of reference values for aerodynamic coefficients. + + + + + + + + + + + + Reference area + + + + + + + Reference length + + + + + + + Reference point + + + + + + + Reference translation + + + + + + + Reference rotation + + + + + + + + + + + + + + Aerodynamic contributions of the components + + + + Contains a list of components for which aerodynamic coefficients are specified + + + + + + + + + + + + + + + + + + + + Aerodynamic contributions of a component + + + + Describes the contributions of a specific component to the total aerodynamic coefficients + + + + + + + + + + + + Reference to a component + + + + + + + + + + + + + + + Aerodynamic contributions of a wing segment + + + + + Describes the contributions of a specific wing segment to the total aerodynamic coefficients of a wing + + + It is obligatory to reference a segment via its + uID + and to provide its + coefficients + . The breakdown of the coefficients comprises the + strips + and + remainingContributions + . The latter must only be specified if + strips + is given. + + + + + + + + + + + + + Reference to a wing segment uID + + + + + + + + + + + + + + + + + + + Aerodynamic contributions of strips within a wing segment + + + + Contains a list of strips within a wing segment for which aerodynamic coefficients are specified + + + + + + + + + + + + + + + + + + + + Aerodynamic contributions of a strip within a wing segment + + + + + Describes the contributions of a specific strip within a wing segment to the total aerodynamic coefficients of a wing segment + + + The strip extends spatially between two + eta + coordinates (i.e., + from + an inner border + to + an outer border). + In order to avoid redundancy, the inner border (denoted as + from + ) is always identical to the outer border of the previous strip (denoted by + to + ). + Accordingly, only the + to + -border can be specified explicitly, while the + from + -border equals implicitly either to + 0 + (for the first strip) or the + toSegmentEta + value of the previous element. The + toSegmentEta + of the last + strip + must be equal to 1! + + + It is obligatory to provide the + coefficients + of the + strip + . The breakdown comprises the + chordwiseParts + and + remainingContributions + . The latter must only be specified if the breakdown into + chordwiseParts + is given. This breakdown is optional. If it is specified, but the sum of all chordwiseParts does not match the strip coefficients, one or more + remainingContributions + may be applied + to ensure consistency (sum of all + chordwiseParts + + sum of all + remainingContributions + must be equal to total strip coefficients). + + + + + + + + + + + + + Spanwise coordinate eta in the segment coordinate system to define the end of the strip + + + + + + + + + + + + + + + + + + + + Aerodynamic coefficients breakdown + + + + + Breakdown of the total aerodynamic coefficients into contributions + from the various vehicle componenents. A detailed breakdown is only specified + for the wing. Other components, such as the fuselage, are more generically + referred to as + otherComponents + . Since + the sum of the contributions within a breakdown must equal the total + coefficients, the remaining contributions must be listed in + remainingContributions + . + + + The + remainingContributions + cannot be defined alone. Either the + definition of a + wing + , + otherComponents + or both together is valid and can be combined with + remainingContributions + . + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Aerodynamic contributions of wing segments + + + + Contains a list of wing segments for which aerodynamic coefficients are specified + + + + + + + + + + + + + + + + + + + + Aerodynamic contributions of the wings + + + + Contains a list of wings for which aerodynamic coefficients are specified + + + + + + + + + + + + + + + + + + + + Aerodynamic contributions of a wing + + + + + Describes the contributions of a specific wing to the total aerodynamic coefficients of a vehicle + + + It is obligatory to reference a wing via its + uID + and to provide its + coefficients + . The breakdown of the coefficients comprises the + segments + and + remainingContributions + . The latter must only be specified if + segments + is given. + + + + + + + + + + + + + Reference to a wing uID + + + + + + + + + + + + + + + + + + + commandCaseCommandType + + + single commandCaseCommand can either hold a + controlFunction or a controlDistributor + + + + + + + + + + + + + + + + + + + + + + + commandCasesType + + + plural Element for commandCase, some fixed dp, dq, dr + and dx, dy, dz + + + + + + + + + + + + + + + + + + + + + + + + + commandCaseType + + + single commandCase Containing several + commandCaseCommands + + + + + + + + + + + + + + + + + + + + + + + + UIDs of 2d structural fuselage elements + (e.g., pressure bulkheads, walls or + floors). The compartment will be + enclosed with the fuselage skin + + + + + + + + + + + + + + + + + + The compartment defines an enclosed volume within the fuselage. It is defined by a set of border geometries. This could be pressureBulkheads, walls or floors and they are referred by their uIDs. The volume is closed with the fuselage skin. The geometry tool has to check, if the compartment definition gives a closed geometry. + + + + + + + + + + + The compartment defines an enclosed volume in the + fuselage. It is defined by a set of border geometries. + This could be pressureBulkheads, walls or floors and + they are referenced by their uIDs. The volume is closed + with the fuselage skin. The geometry tool has to check, + if the compartment definition gives a closed geometry. + + + + + + + + + Compartment geometry uIDs list. + + + + + + + Name of the compartment. + + + + + + + Description of the compartment. + + + + + + Ideal design volume of the compartment. + + + + + + + + + + + + + + + + + + + + + complexBaseType + + + Base type for complex nodes (including external data + attributes) + + + + + + + + + + + + + + + componentCostType + + + + + + + + + + + + + + + + + + + + + + componentSegmentPathType + + + + + + + + + + + + + Definition of hingePoint of the + componentSegment. The hingePoint is used as reference point for + the deflection definition. + + + + + Definition of the orientation of the hinge + line with three Euler-rotation angles. The hinge line is + oriented along the global y-axis if all rotations are 0. + + + + + + Definition of all steps of the deflection + path. + + + + + + + + + + + + + componentSegmentStepsType + + + + + + + + + + + + + Definition of one step of the deflection path. + + + + + + + + + + + + + + componentSegmentStepType + + + + + + + + + + + + + The control parameter is used to reference the + state of a control device, e.g. in the load + case description. Can have any value and is NOT limited to the + range of -1 to 1. + + + + + Translation along the x-, y- and z-Coordinate + of the rotated hinge coordinate system. + + + + + Rotation around the hinge line. + + + + + + + + + + + + + + ComponentSegments of the wing. + + + ComponentSegments type, containing all the + componentSegments of the wing. + + + + + + + + + + + + + + + + + + + ComponentSegment of the wing. + + + + Within componentSegments the wing structure, the + control surfaces, the wing fuel tanks and the + wingFuselageAttachment is defined by using relative coordinates. + + A componentSegment is defined in the same way as + segments: from one cross section (sections->elements) to + another. Compared to segments one componentSegment can can start + and end at elements that are not consecutive. Therefore that one + componentSegment can be the combination of several segments. + Each wing has at least one componentSegment (from root to tip). + The maximal number of componentSegments equals the number of + segments (each segment is defined as one componentSegment). + This also implies that each segment can only be part of one componentSegment. + + In principal a componentSegment can combine any number + of segments. But if in one section two elements are defined, the + componentSegment has to start/end there as no well-defined + relative coordinates can be defined if steps in the wing occur. + + An example for wing componentSegments can be found in + the picture below: + + + + Within componentSegments a relative spanwise + coordinate (eta) and a relative chordwise coordinate (xsi) is + defined. Those coordinates are used for the definition of e.g. + wing structures and control surfaces. there are two types of eta xsi coordinates. + Segment (eta, xsi) coordinates define the relative local coordinate system for a segment ranging from (0,0) to (1,1). + + + + + + The eta xsi coordinates for a component segment are based on the segment eta xsi planes. + As a reference length for the component segment eta coordinate the + mid chord lines of all the segments are used. + The beginning of this line at from-element equals eta = 0, while the end of this line + at the to-element equals eta = 1. All wing positions that lie on the same + element (segment border) have the same eta coordinate. The points in between + two elements are defined by the iso xsi lines of the segment eta xsi space. + An example for the definition of the relative axes can + be found in the picture below: + + + + + In order to calculate the global coordinates of a component segment eta xsi point + one first has to calculate the eta point on the xsi iso line of (xsi=0.5), + and then walk along the iso eta lineof the segment. + + An example for determining the a component + eta xsi point can be found in the picture below: + + + + + + + + + + + + + + + + + + + + + + + + Name of the wing componentSegment. + + + + + + + Description of the componentSegment. + + + + + + + Reference to the element from which the + componentSegment shall start. + + + + + + + Reference to the element from which the + componentSegment shall end. + + + + + + + + + Description of deflection path of + componentSegments (e.g. used for + trimmable HTPs). + + + + + + + + + + + + + + + + + + + Components + + + + + + + + + + + + + + + + + + + Component + + + + + + + + + + + Name + + + + + + + Description + + + + + + + + Link to pre-defined system element uID + + + + + + + Link to pre-defined system element uID + + + + + + + + + + + + + + + + + + compositeLayerType + + + CompositeLayer type, containing data of a composite + layer + + + + This type defines single composite layers by + giving a ply thickness, ply reference angle and a materialUID. + + + + + + + + Name of layer + + + + + Description of layer + + + + + Thickness of layer + + + + + Angle of layer in degree + + + + + Material UID of the layer + + + + + + + + + + + + + compositesType + + + + + + + + + + + + + + + + + + + + + + compositeType + + + Composite type, containing data of a composite + + + + + Within this type individual stackings of + composites can be introduced by defining an offset and a set of + composite layers. The order of the composite layers defines the + stacking order. + + + + + + + Name of composite + + + + + Description of composite + + + + + offset of the laminate. The reference plane of + the laminate is the arithmetic mean of the laminate thickness. + + + + + + + + + + + + + + + + Vehicle configurations + + + + List of vehicle configurations (e.g., setting of control surfaces, landing gear, etc.) + + + + + + + + + + + + + + + + + + + + Vehicle configuration + + + + + + + + + + + Name + + + + + + + Description + + + + + + + + + + + + + + + + + + + Configurations + + + + + + + + + + + + + + + + + + + + + + Configuration + + + + + + + + + + + + + UID of the configuration definition + + + + + Index of the weight and balance vectors to which the configuration applies to. [1;inf] + + + + + + + + + + + + + Configuration + + + + Contains references to control control devices and (or) the global aircraft configuration node. + + + + + + + + + + + + + Reference to the aircraft configuration definition node (aircraft/model/configurationDefinitions/configurationDefinition) + + + + + + + State description of the control elements + + + + + + + + + + + + + + connectivitiesType + + + + + + + + + + + + + + + + + + + + + + connectivityType + + + + + + + + + + + + + + + + + + + + + + + + + Constraint + + + + + Specification of performance constraints. + + + Constraints allow vectors of double values to define parameter lapses within a mission segment. The example below illustrates this by means of an exemplary climb profile of a conventional airliner, in which multiple physical and regulatory speed constraints are simultaneously specified over several altitudes (e.g., to account for the + crossover altitude + ): + + <endCondition> + <positionGeo> + <altitude relationalOperator="ge" uID="altClimb">10058.4</altitude> <!-- FL330 --> + </positionGeo> +</endCondition> +<constraint> + <referenceEndConditionUID>altClimb</referenceEndConditionUID> + <endConditionRatio>0.0;0.303</endConditionRatio> <!-- FL0, FL100 --> + <continuitySetting>discrete</continuitySetting> + <CAS relationalOperator="le">128.61;154.33</CAS> <!-- 250 [kt], 300 [kt]--> + <machNumber relationalOperator="le">0.78;0.78</machNumber> + <prioritySetting>velocity</prioritySetting> +</constraint> + + + From FL0 until FL100, the vehicle should fly at a velocity less than or equal to CAS = 250 kt or M = 0.78. In this first segment at low altitudes, the constraint on CAS is triggered. + + + From FL100 until FL330, the vehicle should fly at a velocity less than or equal to CAS = 300 kt or M = 0.78. In this second segment, the vehicle starts by increasing velocity until 300 kt, the constraint on maximum machNumber triggers from the crossover altitude onwards + + + + + + + + + + + + + Reference to the uID of the segment end condition variable to which a profile of constraintSettings is provided + + + + + + + Vector indicating the ratios of the constraintSettings profile with respect to the provided referenceEndCondition, ranging from 0 to 1. If this vector is defined, the provided constraintSettings are expected to be vectors with the same length providing ratio-value pairs. Example: for referenceEndCondition <range><z> (i.e.: flown distance in z direction of the segment), a vector of <CAS> and <machNumber> is provided to define a climb profile. + + + + + + Defines how to interpret the parameter lapses within the segment: discrete steps (C0 continuity) or linear interpolation (C1 continuity) + + + + + + + + + + + + + + + Calibrated airspeed within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Mach number within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Climb angle within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Rate of climb within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Specific excess power within the segment + (e.g.: for defining minimum SEP to + remain after step climbs have been + performed). + + + + + + + Altitude difference of each step climb + + + + + + + + Flight heading at the end of the segment in compassAngle with reference to true North [deg]. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Total change of heading angle during segment (a full turn is 360 degrees) [deg]. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + + Rate of turn within the segment [deg/s]. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Thrust setting for derated engine as fraction of max. Thrust (e.g.: for powered descents, deceleration not at IDLE, manoevres). If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Rate of velocity within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Load factor experienced during segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Constant altitude of the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + Priority setting indicating which constraint is preferred within the segment. If a vector is provided, a constraint profile is defined with respect to the <referenceEndCondition> using the <endConditionRatio> vector. + + + + + + + + + + + + + + + + + + + + + Mission segment constraints + + + Contains a set of constraints for the segment + + + + + + + + + + + + + + + + + + + Airfoil definition of an control surface at the + inner/outer border. + + + + Optional definition of the exact airfoil shape at the + inner/outer border of the control surface. + The airfoil shape is defined via referencing to the + airfoilUID. As the leading and trailing edge point is fix due to + the outer shape definition of the control surface the airfoil + can only be rotated around the x-axis (axis going from leading + to trailing edge of the inner/outer border of the control + surface). Scaling in x-direction is also defined by the outer + shape, wherefore only scaling in y and z direction is allowed. + + + + + + + + + + + + Reference to the airfoil uID. + + + + + + Rotation around an axis, going from the + leading edge point to the trailing edge point of the inner/outer + border of the control surface. Defaults to 90°, which is + equivalent to perpendicular on the control surface middle plane. + + + + + + Scaling of the airfoil in spanwise direction + (not used for 2D airfoils). + + + + + Scaling in thickness direction of the airfoil. + + + + + + + + + + + + + + controlDistributorsType + + + plural Element for controlDistributor + + + + + + + + + + + + + + + + + + + controlDistributorType + + + + single controlDistributor bundling several + controlElements + Within some analyses, it might occur that overlapping control element settings are specified. In this case, + it is assumed that a cumulative setting is built by summing up the individual settings. As the behavior of these settings + is not necessarily linear, a certain order of summation has to be followed: + + + The command inputs for each + controlDistributor + , coming from the + configurationUID + , as well as from separate settings have to be summed up to a total + commandInput + . + + + With this total + commandInput + , each corresponding + controlDistributor + definition has to be evaluated, in order to get + controlParameter + settings for a number of + controlDevices + . + + + All + controlParameter + settings for a + controlDevice + , coming from the + configurationUID + , from the + controlDistributors + and from separate + controlDevice + settings have to be summed up to get a total + controlParameter + for each controlDevice. + + + With this total + controlParameter + , each corresponding + controlDevice + definition has to be evaluated, in order to find out what the control device finally is doing. + + + During the summation process (depending on the order of processing within step 1 to 4), + commandInputs + or + controlParameters + might exceed the specified limits for that + controlDistributor + or + controlDevices + . As an intermediate result, this should be accepted – however, when it comes to evaluation in step 2 and 4, all + commandInputs + and + controlParameters + have to be within the specified limits. + + + + + + + + + + + + + + + Vector of command inputs. The minimum and maximum value is given by the lowest and highest entry of the vector, respectively. + + + + + + + + + + + + + + + controlElementsType + + + plural Element for controlElement + + + + + + + + + + + + + + + + + + + controlElementType + + + Single controlElement linking the inputs of a controlDistributor via a gain + table to a control device by using its uID. Controls can be ControlSurfaces and in the + future thrust. + + + + + + + + + + UID of the control device, e.g. a control surface. It is not allowed to reference another control distributor. + + + + + Vector of control device states resulting from the input commands. It must be of the same length as the inputCommands element. + The minimum and maximum values are defined according to the minimum and maximum values of the input commands. + + + + + + + + + + + + + controlFunctionsType + + + plural Element for controlFuntion + + + + + + + + + + + + + + + + + + + controlFunctionType + + + single controlFunction containing the controller's + parameters + + + + + + + + + + + + + + + + + + + + + + + + + + Controllability requirements + + + Contains a list of controllability requirements + + + + + + + + + + + + + + + + + + + + Controllability requirement + + + + + + + + + + Name + + + + + Description + + + + + UID of point performance definition + + + + + UID of weight and balance description + + + + + + + + + + + + + + + + controlLawModesType + + + Control Laws type, containing the aircraft's control + law modes + + + + + + + + + + + + + + + + + + + controlLawModeType + + + Control Laws type, containing the aircraft's control + law mode + + + + + + + + + + + + + + + + + + + controlLawsType + + + Control Laws type, containing the aircraft's control + laws + + + + + + + + + + + + + + + + + + + + Definition of actuators of the control surface, that + are not placed within a track. + + + Definition of actuators of the control surface, that + are not placed within a track. + + + + + + + + + + + + + + + + + + + Definition of an actuator of the control surface, that + is not placed within a track. + + + Definition of an actuator of the control surface, that + is not placed within a track. + + + + + + + + + + Reference to the actuator (actuator definition + currently not available in CPCAS, status 1.6). + + + + + + + + + + + + + + + + Airfoil definition of an control surface between inner + and outer border. + + + + Optional definition of the exact airfoil shape between + the inner and outer border of the control surface. + The airfoil shape is defined via referencing to the + airfoilUID. As the leading and trailing edge point is fix due to + the outer shape definition of the control surface the airfoil + can be rotated around the x-axis (axis going from leading to + trailing edge of the control surface) and around the z-axis + (normal axis on the control surface middle plane). Scaling in + x-direction is also defined by the outer shape, wherefore only + scaling in y and z direction is allowed. + + + + + + + + + + + Relative spanwise coordinate (eta) of the + control surface, where the leading edge of the airfoil is + placed. + + + + + Reference to the airfoil uID. + + + + + + Rotation around an axis, going from the + leading edge point to the trailing edge point of the control + surface. Defaults to 90°, which is equivalent to perpendicular + on the control surface middle plane. + + + + + Rotation of the airfoil around the control + surface middle plane normal direciotn. Reference point is the + most forward point of the airfoil. Defaults to 90°, which is + equivalent to the airfoilplacement in flight direction (along + wings-x axis). + + + + + Scaling of the airfoil in spanwise direction + (not used for 2D airfoils). + + + + + Scaling in thickness direction of the airfoil. + + + + + + + + + + + + + + Inner/outer border of the control surface. + + + + Definition of the inner/outer border of the control + surface. + The position on the planform of the control surface is + defined by defining the eta/xsi coordinates of the inner/outer + and forward/rear border. The eta/xsi coordinates refer to the + parent. + In addition, optionally, the airfoil shape of the + control surface can be defined closer. For the leading edge + devices 'hollow'. If an exact control surface airfoil definition + should be used, outerShape->airfoils can be used. + Please find below an example for the definition of the + planform of a trailing edge device. Other controlsurfaces are + similar. + + + + + + + + + + + + + + + + + Relative spanwise inner/outer position of the + leading edge of the control surface. + + + + + Relative spanwise inner/outer position of the + trailing edge of the control surface. Defaults to 'etaLE'. + + + + + + Relative chordwise inner/outer position of + the trailing edge of the control surface. Reference is eta/xsi + from the parent. + + + + + + + + + + + + + + + + + + + + + + + Inner/outer border of the control surface. + + + + Definition of the inner/outer border of the control + surface. + The position on the planform of the control surface is + defined by defining the eta/xsi coordinates of the inner/outer + and forward/rear border. The eta/xsi coordinates refer to the + parent. + In addition, optionally, the airfoil shape of the + control surface can be defined closer. For the + spoiler'relHeightLE' is used. If an exact control surface + airfoil definition should be used, outerShape->airfoils can + be used. + Please find below an example for the definition of the + planform of a trailing edge device. Other controlsurfaces are + similar. + + + + + + + + + + + + + + + + + Relative spanwise inner/outer position of the + leading edge of the control surface. Reference is eta/xsi from + the parent. + + + + + Relative spanwise inner/outer position of the + trailing edge of the control surface. Reference is eta/xsi from + the parent. Defaults to 'etaLE'. + + + + + Relative chordwise inner/outer position of the + leading edge of the control surface. Reference is eta/xsi from + the parent. + + + + + Relative chordwise inner/outer position of the + trailing edge of the control surface. Reference is eta/xsi from + the parent. + + + + + + Defines the relative high of lowest point of + the spoiler leading edge, relative to the airfoil height of the + parent at this position. See picture below. + + + + + + + + + + + + + + + + Inner/outer border of the control surface. + + + + Definition of the inner/outer border of the control + surface. + The position on the planform of the control surface is + defined by defining the eta/xsi coordinates of the inner/outer + and forward/rear border. The eta/xsi coordinates refer to the + parent. + In addition, optionally, the airfoil shape of the + control surface can be defined closer. For the trailing edge + device this is done at 'leadingEdgeShape', for the spoiler + 'relHeightLE' is used and for the leading edge devices 'hollow'. + If an exact control surface airfoil definition should be used, + outerShape->airfoils can be used. + Please find below an example for the definition of the + planform of a trailing edge device. Other controlsurfaces are + similar. + + + + + + + + + + + + + + + + + Relative spanwise inner/outer position of the + leading edge of the control surface. Reference is eta/xsi from + the parent. + + + + + Relative spanwise inner/outer position of the + trailing edge of the control surface. Reference is eta/xsi from + the parent. Defaults to 'etaLE'. + + + + + Relative chordwise inner/outer position of the + leading edge of the control surface. Reference is eta/xsi from + the parent. + + + + + + + + + + + + + + + + Optional definition of the exact airfoil shape of the + control surface. + + + + + + + + + + + + + + + + + + + + + + This type contains a list of control surfaces and their + deflection vectors + + + + + 0. General overview + + In this type, a list of control surfaces is defined. + + + + + + 1. + <controlSurface> + (mandatory) + + + One of these nodes per deflected control surface is + required here. + + + + + + + + + + + + + + + + + + + + + + This type contains a vector of deflection values for a + single control surface + + + + + 0. General overview + + In this type, a vector of deflections of a single + control surface is specified. + + + + + 1. + <controlSurfaceUID> + (mandatory) + + + A reference to a control surface from the aircraft + model + + + + + 2. + <controlParameters> + (mandatory) + + + A vector of controlParameters of the selected + control surface (with respect to the defined deflection path). + + + + + + + + + + + + + + Reference to a control surface + + + + + + Control parameters of the control surface + + + + + + + + + + + + + + controlSurfaceHingeMomentMapsType + + + controlSurfaceHingeMomentMapsType type, containing the + aerodynamic moment maps for one or more control surfaces. + + + + + + + + + + + + + + + + + + + + controlSurfaceHingeMomentMapType + + + controlSurfaceHingeMomentMap type, containing a moment + map with aerodynamic data for a control surface. Array order is: + controlParameters min->max then angleOfAttack then angleOfSideslip + then reynoldsNumber then machNumber. AngleOfAttack, angleOfSideslip, + reynoldsNumber and machNumber are taken from the basic + performance map one level above. + + + + + + + + + + Reference to the control surface + + + + + + Control parameters of the control surface + + + + + + + + + + + + + + + + + + + + controlSurfaceHingePointType + + + + The deflection path of a control surface is described + with respect to two hinge points - one at the inner border of + the control surface and one at the outer border of the control + surface. Those two points are defined using the xsi and relative + height coordinates of the parent. Therefore those points can also + lay outbound of the control surface. Those two points defined + the hinge line, which is a straight line between the two points. + + An example can be found below: + + + + + + + + + + + + + + Relative chordwise coordinate (xsi) of the + hinge line point. Reference is the parent chord. + + + + + + Relative height of the hinge line point. + Reference is the parent airfoil height. + + + + + Optional absolute translation of the hinge point. + This can be used to move the hinge points outside of the wing shape. + + + + + + + + + + + + + Outer shape definition of the control surface. + + + + + Definition of the outer shape of the leading edge + control surface. + The position on the planform of the control surface is + defined by defining the eta/xsi coordinates of the inner/outer + and forward/rear border. The eta/xsi coordinates refer to the + parent. + Please find below an example for the definition of the + planform of a trailing edge device. Other controlsurfaces are + similar. + + + + + + + + + + + + + + + + + + + + + + + + + Outer shape definition of the spoiler control surface. + + + + + Definition of the outer shape of the control surface. + + The position on the planform of the control surface is + defined by defining the eta/xsi coordinates of the inner/outer + and forward/rear border. The eta/xsi coordinates refer to the + parent. + Please find below an example for the definition of the + planform of a trailing edge device. Other controlsurfaces are + similar. + + + + + + + + + + + + + + + + + + + + + + + + + Outer shape definition of the control surface. + + + + + Definition of the outer shape of the trailing Edge + control surface. + The position on the planform of the control surface is + defined by defining the eta/xsi coordinates of the inner/outer + and forward/rear border. The eta/xsi coordinates refer to the + parent. + Please find below an example for the definition of the + planform of a trailing edge device. Other controlsurfaces are + similar. + + + + + + + + + + + + + + + + + + + + + + + + + Definition of the deflection path of the control + surface. + + + + The deflection path of a control surface is described + with respect to two hinge points - one at the inner border of + the control surface and one at the outer border of the control + surface. Those two points are defined using the xsi and relative + height coordinates of the parent. Therefore those points can also + lay outbound of the control surface. Those two points defined + the hinge line, which is a straight line between the two points. + + The deflection path of the control surface is defined + within the hinge line coordinat system. This is defined as + follows: The x-hinge coordinate equals the wing x-axis. The + y-hinge coordinate equals the hinge line axis (see above; + positive from inner to outer hinge point). The z-hinge line is + perpendicular on the x-hinge and y-hinge coordinate according to + the right hand rule. The rotation of the control surface is + defined as rotation around the positive y-hinge line. + + The deflection of the is defined in any number of + steps. The deflection of the control surface is done as follows: + First the x-deflection at the inner and outer border; afterwards + the z-deflection of the inner and outer border; last the + y-deflection of the inner border. The y-deflection is only + defined at the inner border, as it is identical to the outer + border. If no values for the outer border deflection are given, + they default to the values of the inner border. + An example can be found below: + + + + + + + + + + + + + + + + + + + + + + + + + controlSurfacePerformanceMapType + + + ControlSurfacePerformanceMap type, containing a delta + performance map with aerodynamic data for a control surface. Array + order is: relativeDeflection min->max then angleOfAttack then + angleOfSideslip then altitude then machNumber. AngleOfAttack, + angleOfSideslip, altitude and machNumber are taken from the + basic performance map one level above. + + + + + + + + + + Reference to the control surface + + + + + + Relative deflection of the control surface + + + + + + + + + + + + + + + + + + + + controlSurfacePerformanceMaps + + + controlSurfacePerformanceMaps type, containing the + aerodynamic delta performance maps for one or more control + surfaces. + + + + + + + + + + + + + + + + + + + Border type for the inner and outer border of a wing + cut out + + + + Maybe applied to specify inner and outer border of + the cutout either via eta or rib references + + + + + + + + + + + + + + + Link to a rib definition + + + + + + Rib number in the corresponding + ribDefinitionUID + + + + + + + Spanwise location of the border at the + leading edge of the cut out + + + + + Spanwise location of the border at the + trailing edge of the cut out + + + + + + + + + + + + + + Cut out of the parents upper/lower skin due to a + control surface. + + + + Optional. Definition of the skin cut out due to a + control surface. The cut out of the skin can either be defined + by referencing to a spar uID or by defining the relative chord + values (xsi) of the cut at the inner and outer border of the + control surface. The xsi value is based on the parents chord. + For leading edge devices additional parameters can be defined. + + An example for wing cut outs can be found in the + picture below: + + + + + + + + + + + + + + + Xsi value of the inner border, where the cut + out begins. + + + + + Xsi value of the outer border, where the cut + out begins. + + + + + + Reference to a spar, defining the skin cut + out. + + + + + + + + + + + + + Definition of the steps of the control surface + deflection path. + + + + List of steps. + + + + + + + + + + + + + + + + + + + + controlSurfaceStepType + + + + The deflection path of the control surface is defined + within the hinge line coordinat system. This is defined as + follows: The x-hinge coordinate equals the wing x-axis. The + y-hinge coordinate equals the hinge line axis (see above; + positive from inner to outer hinge point). The z-hinge line is + perpendicular on the x-hinge and y-hinge coordinate according to + the right hand rule. The rotation of the control surface is + defined as rotation around the positive y-hinge line. + + The deflection of the is defined in any number of + steps. The deflection of the control surface is done as follows: + First the x-deflection at the inner and outer border; afterwards + the z-deflection of the inner and outer border; last the + y-deflection of the inner border. The y-deflection is only + defined at the inner border, as it is identical to the outer + border. If no values for the outer border deflection are given, + they default to the values of the inner border. + An example can be found below: + + + + + + + + + + + + + + The control parameter links a generic floating point value to + a certain status of a control device (e.g. control surface, landing gear, suction + system, brake parachute, ...). See the documentation of the global CPACS-Element for + further information. + + + + + + Translation of the inner hinge line point + within the hinge line coordinate system. Defaults to zero. Not + allowed for spoilers! + + + + + Translation of the outer hinge line point + within the hinge line coordinate system. Defaults to the values + of the inner hinge line point. Not allowed for spoilers! + + + + + + Positive rotation around the hinge line, + heading from the inner to the outer border. Defaults to zero. + + + + + + + + + + + + + + controlSurfacesType + + + Definition of the outer shape, structure and deflection + of all control surfaces (flaps, slats, soiler, ailerons...) of + the wing. + + + + + + + + + + + + + + + + + + + + + Control surface tracks (mechnaical link between control + surface and parent). + + + + + + + + + + + + + + + + + + + + + + Control surface tracks (mechnaical link between control + surface and parent). + + + + + A + track + generally describes the structural connection between a control surface and a wing (or parent element). For example, a track can be a flap track, a revolute joint connecting an aileron or spoiler, or the kinematics of slats on a wing. + + + The spanwise position of the track is defined by + etaPosition + , which refers to the control surface dimensions. + + + The structural properties of the track (e.g. + materials) are defined in + trackStructure + . + + + If an actuator is included into the the track, a + reference is given in + actuator + . + + + The principal kinematic of the track is defined by + setting the + trackType + and + trackSubType + . Please refer to the + tables below for setting the + trackType + and + trackSubType + parameter. Note, those tables are not final - they are extended + continuously. + + + + + Trailing edge track types + + + trackType + picture + description + trackSubType + picture + description + + + 1 + + + + + + Revolute joint; no actuators; the revolute joint is on TED hinge line. + 1 + + + + + + Revolute attached at the wings rear spar and the TEDs front spar respectively the load + carrying ribs of the TED. + + + 2 + + + + + + Revolute joint; dropped hinge; linear or rotary actuator (subtype-dependent) included. + The drive strut (if any) is defined as strut1. + 1 + + + + + + Box beam design as wing attachment; rotary drive attached at wing rear spar. + + + + + + 2 + + + + + + Wing attachment at wing rear spar; rotary drive attached at wing rear spar + + + + + + 3 + + Track mounted inside the fuselage at wing root. + + + 3 + + + + + + Upside-down, forward link in conjunction with a straight track on a fixed structure + as aft. support; including rotary drive. + 1 + + + + + + Wing attachment using a box beam design where track is mounted; rotary actuator mounted + at the wing rear spar. + + + + + + 2 + + Track mounted inside the fuselage at wing root. + + + 4 + + + + + + Straight and sloped track on a fixed structure as forward support and an upright link as + aft. support; linear or rotary actuator (subtype-dependent) included. + 1 + + + + + + Wing attachment using a box beam design where the track is mounted; rotary actuator at + the wing rear spar. + + + + + + 2 + + + + + + Wing attachment using a box beam design where track is mounted; rotary actuator mounted + on the track. + + + + + + 3 + + Track mounted inside the fuselage at wing root. + + + + + + + + + + + + + + Relative chordwise position of the track. Eta + refers to the control surface. + + + + + Type of the track. Please refer to the remarks + of the controlSrufaceTrackTypeType for details. + + + + + + + + + + + + + + + + Type of the track. Please refer to the remarks + of the controlSrufaceTrackTypeType for details. + + + + + + + + + + + + + + + + + + + + + + + + + + Cut out of the parents structure due to a control + surface. + + + + Optional. Definition of the parents structure cut out + due to a control surface. The cut out is split into three parts: + cut out of the upper and lower skin and the definition of an + profile connecting the cut out of the upper and lower skin. + + An example for wing cut outs can be found in the + picture below: + + + + In the default configuration the cut out is as wide as + the control surface. If additional spacing is necessary inner + and outer border may be set. + + + + + + + + + + + + + + + + + + + + + + + + + costAirConditioningSystemsType + + + + + + + + + + + + + + + + + + + + + + + costAutomaticFlightSystemsType + + + + + + + + + + + + + + + + + + + + + + + costAuxilaryPowerUnitsType + + + + + + + + + + + + + + + + + + + + + + + costBleedAirSystemsType + + + + + + + + + + + + + + + + + + + + + + + costCommunicationSystemsType + + + + + + + + + + + + + + + + + + + + + + + costComponentsType + + + + + + + + + + + + + + + + + + + + + + + + + + costDeIcingSystemsType + + + + + + + + + + + + + + + + + + + + + + + costElectricalSystemsType + + + + + + + + + + + + + + + + + + + + + + + costEnginePylonsType + + + + + + + + + + + + + + + + + + + + + + + costEquippedEnginesType + + + + + + + + + + + + + + + + + + + + + + + costFireProtectionSystemsType + + + + + + + + + + + + + + + + + + + + + + + costFixedEmergencyOxygenSystemsType + + + + + + + + + + + + + + + + + + + + + + + costFlightControlSystemsType + + + + + + + + + + + + + + + + + + + + + + + costFuelSystemsType + + + + + + + + + + + + + + + + + + + + + + + costFurnishingElementsType + + + + + + + + + + + + + + + + + + + + + + + costFurnishingsType + + + + + + + + + + + + + + + + + + + + + + + + + + costFuselagesType + + + + + + + + + + + + + + + + + + + + + + + costHydraulicSystemsType + + + + + + + + + + + + + + + + + + + + + + + costInstrumentSystemsType + + + + + + + + + + + + + + + + + + + + + + + costLandingGearType + + + + + + + + + + + + + + + + + + + + + + + costLightingSystemsType + + + + + + + + + + + + + + + + + + + + + + + costNacellesType + + + + + + + + + + + + + + + + + + + + + + + costNavigationSystemsType + + + + + + + + + + + + + + + + + + + + + + + costPowerUnitsType + + + + + + + + + + + + + + + + + + + + + + + + + + costSystemsType + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + costWaterInstallationSystemsType + + + + + + + + + + + + + + + + + + + + + + + costWingsType + + + + + + + + + + + + + + + + + + + + + + + crashLoadCasesType + + + + + + + + + + + + + + + + + + + + + + crashLoadcaseType + + + CrashLoadcase type, containing a crash loadcase + + + + + + + + + + + + + Optional start of crash section: Default: + first frame of model + + + + + Optional end of crash section: Default: last + frame of model + + + + + Initial velocities + + + + + Initial rotations around axes, roll, pitch, + yaw + + + + + Initial rotational velocities around axes + + + + + + Definition of reference point to consider + rotation + + + + + AccelerationFields, usually gravity in z + + + + + + Definition of impact Surface for crash + simulation + + + + + + + + + + + + + + + + + + + + + + + crewCostType + + + + + + + + + + + + + + + + + + + + + + + + crossBeamAssemblyPositionType + + + CrossBeamAssemblyPosition type, containing the position + of a crossBeam assembly + + + + + + + + + + UID of profile based structural element to be + used as crossbeam + + + + + UID of the frame to which the crossbeam is + attached + + + + + Referenze z position of the crossbeam + + + + + + + + + + + + + + + + crossBeamStrutAssemblyPositionType + + + CrossBeamStrutAssemblyPosition type, containing a + crossBeam strut assembly position + + + + + + + + + + UID of profile based structural element to be + used as crossbeam strut + + + + + UID of the frame to which the crossbeam strut + is attached + + + + + UID of the crossbeam to which the crossbeam + strut is attached + + + + + Referenze y position of the strut at the + crossbeam intersection + + + + + angle of the strut in global yz plane + + + + + + + + + + + + + + + + cruiseRollersType + + + + + + + + + + + + + Definition of one cruise rollers/mid-span + stops. + + + + + + + + + + + + + cruiseRollerType + + + + + + + + + + + + + Definition of the position of the mid point of + the roll of the cruise roller. + + + + + Definition of the attachment of the cruise + roller to the parent of the flap. This is the track on which the + roll rolls during retracted flap position + + + + + Definition of the attachment of the cruise + roller to the flap. + + + + + Degree of freedom that is blocked by the + cruise roller if the flap is in retracted position. Positive = + cruise roller blocks bending in the direction of the upper skin + of the parent. Negative = cruise roller blocks bending in the + direction of the lower skin of the parent. + + + + + + + + + + + + + + cst2DType + + + + + + + + + + + A 2D implementation for Class shape + transformations. For more details look at AIAA Journal of Aircraft + Vol.45 No.1 2008 + + + + + The psi vector for definition of the class and + shape function, i.e. the points at which the CST functions will + be evaluated + + + + + N1 for the class function for the upper side + of the profile + + + + + N2 for the class function for the upper side + of the profile + + + + + B Coefficients for the Bernstein polynominal + on the upper side + + + + + N1 for the class function for the lower side + of the profile + + + + + N2 for the class function for the lower side + of the profile + + + + + B Coefficients for the Bernstein polynominal + on the lower side + + + + + Optionally, the trailingEdgeThickness of the + profile + + + + + + + + + + + + + Cuboid + + + + + + + + + + Length [m] + + + + + Width [m] + + + + + Height [m] + + + + + + + + + + + + + Maps points (actually the index in the point list) to a curve parameter. + + + + Which parameters are allowed depends on the context. + For example in a wing profile, values between -1 and 1 are valid. + + + + + + + + + + + List of indices of points to be mapped. Each index must be in the range [1, npoints]. + + + + + List of parameters on the curve, that is mapped to the points defined by their index. + + + + + + + + + + + + + A curve that interpolates a list of points. + + + + The curve interpolates the list of points, typically with a b-spline. + In theory, the interpolation is somewhat ambiguous as it is not defined at which + curve parameter a point will be interpolated. + + To solve is ambiguity, an optional parameter map can be defined + that maps point indices with curve parameters. + + Kinks can also be modeled by populating the "kinks" array with the + indices of points that should be on a kink. As an example, look at the following image: + + + + + In this example, the kinks array will be "3;7". + Optionally, the parameters of the kinks can be set in the parameter map. + The whole profile looks as follows: + + +<pointList> + <x>...</x> + <y>...</y> + <z>...</z> + <kinks>3;7</kinks> + <parameterMap> + <pointIndex>3;5;7</pointIndex> + <paramOnCurve>0.2;0.5;0.8</paramOnCurve> + </parameterMap> +</pointList> + + + + + + + + + + + + Indices of points at which the curve has a kink. Each index is in the range [1, npoints]. + + + + + + Map between point index and curve parameter. + + + + + + + + + + + + + curvePointType + + + Point on a curve in normalized curve coordinates. + The referenceUID must reference a one-dimensional curve such as spars. + + + + + + + + + + Relative position on the referenced line/curve. + + + + + This reference uID determines the reference curve. + If it points to a spar, then the eta value is considered to be a spar coordinate + between start (eta=0) and end (eta=1) of the spar. + + + + + + + + + + + + + + + + + + + + + + + cutLoadIntegrationPointsType + + + cutLoadIntegrationPoints are defined in a vector + notation, due to the high amounts of data. Usually they well be + defined in between the ribs. Each point must have an id. + Optionally it is possible to rotate the orientation within a + cutloadIntegrationPoint to obtain meaningful results. The + orientation is optional and relative to the CPACS coordinate + system + + + + + + + + + + + + + + + + + + + + + + + + + cutOutControlPointsType + + + + + + + + + + + + + + + + + + + + + + + Additional definition of the leading edge cut out. + + + + + Optional. Definition of additional parameters, + describing the shape of the parents leading edge of the cut out + due to leading edge devices. + The parameters are described in the picture below: + + + + + + + + + + + + + + + Relative height of the most forward position of + the parents leading edge, relative to the airfoil height without + cut out. + + + + + Relative chordwise position of the most + forward position of the parents leading edge, relative to the + parents chord without cut out. + + + + + + + + + + + + + Definition of cut out profiles. + + + + + + + + + + + + + + + + + + + + + + + + Definition of cut out profiles. + + + + Optional, the exact shape between the upper and lower + skin cut out can be given by using cutOutProfiles. In general + cut out profiles are open profiles and not closed profiles as + e.g. wing airfoils. The placement, scaling and (partly) rotation + of the cut out profiles is fixed as the beginning and ending + point of the profile is fixed as can be seen in the two pictures + below. + + + + + + + + + + + + + + + + + Reference to the profile uID. Profiles should + be linked in profiles/structuralProfiles + + + + + Relative spanwise position of the cut out + profile. The eta coordinate refers to the control surface and + describes the cut out profile at the leading edge of the control + surface. + + + + + Rotation of the airfoil around the control + surface middle plane normal direciotn. Reference point is the + most forward point of the airfoil. Defaults to 90°, which is + equivalent to the airfoilplacement in flight direction (along + wings-x axis). + + + + + + + + + + + + + cutOutType + + + CutOut type, containing cut-outs + + + + + + + + + + Name of the cut out element + + + + + + Description of the cut out element + + + + + + Width of the cut element (absolute value) + + + + + + Height of the cut element (absolute value) + + + + + + Fillet radius of the cut element (absolute + value) + + + + + UID of a structural element that reinforces + the cut out + + + + + + + + + + + + + + Damping derivatives for positive and negative rotation + rates + + + + + 0. General overview + + This type contains the damping derivatives. They are + split up into those derivatives for positive rotation rates, + and those for negative rotation rates. + + + + 1. <positiveRates> (optional) + + Damping derivatives, calculated by positive rotation + rates. + + + + 2. <negativeRates> (optional) + + Damping derivatives, calculated by negative rotation + rates. + + + + + + + + + + + + + + + + + + + + + + + + Damping derivatives for positive and negative rotation rates + + + + + 0. General overview + + This type contains the damping derivatives. They are + split up into those derivatives for positive rotation rates, + and those for negative rotation rates. + + + + 1. <positiveRates> (optional) + + Damping derivatives, calculated by positive rotation + rates. + + + + 2. <negativeRates> (optional) + + Damping derivatives, calculated by negative rotation + rates. + + + + + + + + + + + + + + + + + + + + + + + Damping derivatives + + + This type contains aerodynamic performance maps with + the damping derivatives. The derivatives are calculated using + rotational rates [rad/s], normalized by: + Rate*ReferenceLength/flow speed. The rotations are performed + around the global axis directions with the aircraft model's + global reference point as origin. The damping derivative + performance maps are vectors of the same length as the input + vectors of the baseline aerodynamic performance maps, consisting of + semicolon separated values. + + + + + + + + + + + Change of cd by normalized roll rate + + + + + Change of cd by normalized pitch rate + + + + + Change of cd by normalized yaw rate + + + + + Change of cs by normalized roll rate + + + + + Change of cs by normalized pitch rate + + + + + Change of cs by normalized yaw rate + + + + + Change of cl by normalized roll rate + + + + + Change of cl by normalized pitch rate + + + + + Change of cl by normalized yaw rate + + + + + Change of cmd by normalized roll rate + + + + + Change of cmd by normalized pitch rate + + + + + Change of cmd by normalized yaw rate + + + + + Change of cms by normalized roll rate + + + + + Change of cms by normalized pitch rate + + + + + Change of cms by normalized yaw rate + + + + + Change of cml by normalized roll rate + + + + + Change of cml by normalized pitch rate + + + + + Change of cml by normalized yaw rate + + + + + + + + + + + + + damTolBehaviourType + + + + + + + + + + + + + Damage tolerance law, Walker approach + + + + + Damage tolerance law, Forman approach + + + + + + + + + + + + + damTolFormanType + + + + + + + + + + + + + Parameter Kc [Pa m^0.5] + + + + + Parameter C2 [m/cycle] + + + + + Parameter m2 [-] + + + + + + + + + + + + + damTolWalkerType + + + + + + + + + + + + + Fracture toughness KIc [Pa m^0.5] + + + + + Parameter C0 [m/cycle] + + + + + Parameter m [-] + + + + + Parameter gamma [-] + + + + + + + + + + + + + dateBaseType + + + Base type for date nodes (including external data attributes). + This date type is based on the xsd:date definition. + "To specify a time zone, you can either enter a date in UTC time by adding a "Z" behind the date - like this: 2002-09-24Z + or you can specify an offset from the UTC time by adding a positive or negative time behind the date - like this: + 2002-09-24-06:00 + or + 2002-09-24+06:00" (description taken from http://www.w3schools.com/xml/schema_dtypes_date.asp) + + + + + + + + + + + + + + + + + + + + dateTimeBaseType + + + Base type for dateTime nodes (including external data + attributes) + + + + + + + + + + + + + + + + + + + Deck component + + + + + + + + + + Name + + + + + Description + + + + + UID of the corresponding element in the cpacs/vehicles/deckElemets node + + + + + + + + + + + + + + + + Deck component + + + + + + + + + + Name + + + + + Description + + + + + UID of the corresponding element in the cpacs/vehicles/deckElemets node + + + + + + + + + + + + + + + + Deck doors + + + + + + + + + + + + + + + + + + + + + + Deck door + + + doors describe all doors of the cabin. They are linked + to a structural door description. The cabin door is usually equal + in size to the door, but does not need to be. The structural door + might describe a wider cut-out, while the cabin door is primarily + intended for evacuation modeling and cabin layout. In order to + obtain a 3-dimensional door representation, the local cabin + geometry shall be used. + + + + + + + + + + Name + + + + + Description + + + + + Number of passengers this door adds to the + overall exit capacity limit of the aircraft. + + + + + Opening geometry of the door + + + + + Door type (boarding, cargo, evacuation or service) + + + + + + + + + + + + + + + + + + + + + + + + Deck elements + + + A list of predefined elements which can be linked in the actual deck of the aircraft or rotorcraft model via referencing its uID. + + + + + + + + + + Ceiling panel elements for use in the decks + + + + + Class divider elements for use in the decks + + + + + Galley elements for use in the decks + + + + + Generic floor elements for use in the decks + + + + + Lavatory elements for use in the decks + + + + + Luggage compartment elements for use in the decks + + + + + Seat elements for use in the decks + + + + + Sidewall panel elements for use in the decks + + + + + Cargo container elements for use in the decks + + + + + + + + + + + + + Deck + + + Data of an aircraft or rotorcraft deck + + + + + + + + + + Name + + + + + Description + + + + + UID of the object used as parent coordinate system (typically the fuselage uID) + + + + + UID of the floor structure which supports this deck + + + + + The reference point of the deck/cabin. In a + conventional aircraft like the A320, it would be the rear wall + of the cockpit. The transformation is relative to the parent object + defined by “parentUID”, which should be the fuselage. + + + + + + Deck type: passanger, VIP, cargo or livestock + + + + + + + + + + + + + + + + Seat modules + + + + + Aisles + + + + + Spaces + + + + + Sidewall panels + + + + + Luggage compartments + + + + + Ceiling panels + + + + + Galleys + + + + + Generic floor modules + + + + + Lavatories + + + + + Class dividers + + + + + Cargo containers + + + + + Doors + + + + + + + + + + + + + + Structural mounts + + + Structural mount type containing the structural connections of cabin elements + + + + + + + + + + + + + + + + + + + Structural mount + + + Structural mount type containing the structural connections of cabin elements + + + + + + + + + + Name + + + + + Description + + + + + UID of the component to connect to + + + + + + + + + + + + + + Decks + + + List of decks + + + + + + + + + + + + + + + + + + + + deltaTemperatureType + + + + + + + + + + + + + + + + + + + + + + + + + + + + Design masses + + + The design mases are requerments which can com form the + TLARs + + + + + + + + + + Take off mass + + + + + Zero Fuel mass + + + + + Maximum landing mass + + + + + Maximum ramp mass (the maximum weight + authorised for the ground handling) + + + + + + + + + + + + + Design parameters list + + + Contains a list of all design parameters. + + + + + + + + + + + + + + + + + + + + Design parameter definition + + + Contains a the values of a parameter and its uid as reference. + + + + + + + + + + + + + + + + + + + + + + Design space definition + + + Contains the definition of the design space. + + + + + + + + + + + + + + + + + + + + + + + Design study definitions + + + Contains the data of design studies definitions. + + + + + + + + + + + + + + + + + + + + directOperatingCostType + + + + + + + + + + + + + + + + + + + + + + + + + + + + divergenceCasesType + + + DivergenceCases type, containing the cases for + aeroelastic divergence analysis + + + + + + + + + + + + + + + + + + + divergenceCaseType + + + DivergenceCase type, containing a case for aeroelastic + divergence analysis + + + + + + + + + + Mach number of divergence case + + + + + + Divergence stagnation pressure + + + + + + + + + + + + + + Dome Type + + + + + + + + + + + + + + + + + + + + + + + + + doorAssemblyPositionType + + + DoorAssemblyPosition type, containing the position of a door + assembly + + + + + + + + + + + + optional definition of door type (restricted to pax, + service, emergency, cargo) + + + + + + + + + + + + + + + UID of the door element + description + + + + + UID of the forward door frame + + + + + UID of the backward door frame + + + + + UID of the stringer at the upper door + edge + + + + + UID of the stringer at the lower door + edge + + + + + Lower height of the door with respect to the floor. + (Information necessary for boarding and evacuation analysis not + necessarily linked to structures) + + + + + Minimum widh of the door element. (Information + necessary for boarding and evacuation analysis not necessarily + linked to structures) + + + + + Minimum height of the door element. (Information + necessary for boarding and evacuation analysis not necessarily + linked to structures) + + + + + Door on right side of the fuselage = 1; on the left = + -1. (Information necessary for boarding and evacuation analysis not + necessarily linked to structures) + + + + + + + + + + + + + + doorCutOutType + + + CutOut type, containing cut-outs + + + + + + + + + + Name of door cutout element + + + + + Description of door cutout + element + + + + + Fillet radius of door cutout + element + + + + + Reference UID to the description of a DSS (door + surround structure) + + + + + + + + + + + + + + doorOpeningLegacyType + + + doors describe all doors of the cabin. They are linked + to a structural door description. The cabin door is usually equal + in size to the door, but does not need to be. The structural door + might describe a wider cut-out, while the cabin door is primarily + intended for evacuation modeling and cabin layout. In order to + obtain a 3-dimensional door representation, the local cabin + geometry shall be used. + + + + + + + + + + This is the forward x-coordinate of the door + relative to the cabin origin. + + + + + the door sill height relative to cabin origin. + + + + + + The width of the door in x-direction. + + + + + + the effective height of the door. + + + + + + + + + + + + + + + + + + + + + + + + "doorOpeningType" + + + Ceiling panel instance collection type. + + + + + + + + + + + + + + + + + + + + doorsType + + + Doors type, containing doors + + + + + + + + + + + + + + + + + + + doorSurroundStructurePositionType + + + DoorSurroundStructurePosition type, containing the position of a + door surround structure + + + + + + + + + + + + number of bays effected by DSS in front of + door + + + + + number of bays effected by DSS in behind of + door + + + + + number of bays effected by DSS + + + + + number of bays effected by DSS + + + + + + + + + + + + + + doorSurroundStructuresAssemblyType + + + doorSurroundStructuresAssembly type, containing + dorrSurroundStructure definitions + + + + + + + + + + + + + + + + + + + Array with semicolon separated values of type double + + + + + In + CPACS + arrays are used to exchange values + in full-factorial parameter spaces, for example to describe the aerodynamic coefficients depending + on Mach number and altitude. + + Thus, the dimensions of the array are spanned by the input vectors. See the following + example where two input vectors are defined. For clarification the entries of the array result from + the multiplication of the index values of the corresponding input vectors: + +<inputVector1>1;2;3</inputVector1> +<inputVector2>4;5;6;7</inputVector2> + + +<array>4;5;6;7;8;10;12;14;12;15;18;21</array> + + + Any entries of type + double + separated by semicolons are valid, e.g.: + + +<doubleArrayTest>123.456;+123.456;-1.234e56;-.45E-6;NaN;0</doubleArrayTest> + + +<doubleArrayTest>123.456</doubleArrayTest> + + +<doubleArrayTest>123.456,+1234.456</doubleArrayTest> + + +<doubleArrayTest>123.456;mainWingUID</doubleArrayTest> + + +<doubleArrayTest>1234.4E 56;-1.234e5.6</doubleArrayTest> + + + Please note that the syntax of arrays in the current + CPACS + version correspond exactly to the syntax of vectors. There is no special character indicating + the dimensions. Thus, the input vectors have to be determined from the documentation of the + corresponding elements and splitting of the one-dimensional vector has to be done manually. + + + + + + + + + + + + + + + + + + + doubleBaseType + + + + Base type for double nodes (including external data + attributes) + The double base type can include optional uncertainty + information. The description of uncertainties is placed in + additional attributes. First, it is described by an attribute + that describes the type of uncertainty function called + functionName. The functionName attribute includes the tag name + of the distribution function which is listened in the table + shown below. Each uncertainty function is further describes by a + set of parameters that are described in the table below. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + doubleConstraintBaseType + + + + Base type for double nodes including a relational operator attribute indicating valid constraint region + The doubleConstraintBaseType extends the doubleBaseType and thus inherits all its attributes. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Vector with semicolon separated values of type double + + + + + Any entries of type + double + separated by semicolons are permitted, e.g.: + + +<doubleVectorTest>123.456;+123.456;-1.234e56;-.45E-6;NaN</doubleVectorTest> + + +<doubleVectorTest>123.456</doubleVectorTest> + + +<doubleVectorTest>123.456,+1234.456</doubleVectorTest> + + +<doubleVectorTest>123.456;mainWingUID</doubleVectorTest> + + +<doubleVectorTest>123.456;1234.4E 56;-1.234e5.6</doubleVectorTest> + + + + + + + + + + + + + + + + + + + doubleVectorConstraintBaseType + + + + Base type for double vectors including a relational operator attribute indicating valid constraint region. + The doubleVectorConstraintBaseType extends the doubleVectorBaseType and thus inherits all its attributes. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Drag contributions + + + + The drag contributions relate to different physical mechanisms. The sum of the contributions does not have to be equal to the total drag. + + + + + + + + + + + + Drag contributions due to the displacement of the flow around a component. Zero for irrotational two-dimensional flows. + + + + + + + Drag contributions due to shear forces on surfaces + + + + + + + Drag contributions due to friction + + + + + + + Drag contributions due to energy loss through vortex structures caused by the pressure difference between the upper and lower sides of three-dimensional lifting surfaces. + + + + + + + Drag contributions due to mixing of streamlines between airframe components (e.g., interaction between wing and fuselage or pylon and wing). + + + + + + + Drag contributions due to energy dissipation in shock waves + + + + + + + Drag contributions due to trimmed aircraft configuration + + + + + + + + + + + + + + driveSystemsType + + + DriveSystems Type, containing all the drive systems + (combination of transmissions/gearboxes and shafts and their + links to engines and rotors) of a rotorcraft model. + + + + + + + + + + + + + + + + + + + driveSystemType + + + DriveSystem Type, defining a drive system (combination + of transmissions/gearboxes and shafts and their links to engines + and rotors) of a rotorcraft model. + + + + + + + + + + + + + + + + + + + + + Duct assembly + + + + + + + + + + + Name + + + + + + + Description + + + + + + + UID of part to which the duct is + mounted (if any) + + + + + + + + + + + + + + + + + + Duct structure + + + + + + + + + + + + + + + + + + + + + Ducts + + + + + + + + + + + + + + + + + + + + Duct + + + + + + + + + + + Name + + + + + + + Description + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + dynamicAircraftModelAnalysisType + + + + + + + + + + + + + + + + + + + + + + Electrical energy carriers + + + + + + + + + + + + + + + + + + + Electrical energy carrier + + + + + + + + + + Name + + + + + Description + + + + + Ratio of mass flow per energy flow + + + + + Specific energy + + + + + Density at 15deg C + + + + + Nominal C-Rate + + + + + Maximum C-Rate + + + + + + + + + + + + + + Electric motors + + + + + + + + + + + + + + + + + + + Electric motor + + + + + + + + + + + + + + + Electric power + + + + + + + + + + + Electric power values + + + + + + + + Direct current voltage [V] + + + + + + + + + + + + + + + + Electric power + + + + + + + + + + + Electric power value + + + + + + + + Direct current voltage [V] + + + + + + + + + + + + + + + + Geometry + + + + + + + + + + + + + + + + + + + + + + + Mass + + + Description of mass, center of gravity and inertia. Density should only be specified in combination with a valid geometry. + + + + + + + + + + + + Density + + + + + Mass + + + + + + Center of gravity (x,y,z) + + + + + + + + + + + + + + + Ellipsoid dome + + + + + + + + + + Half axis fraction + + + + + + + + + + + + + Emissivity map, containing the diffuse emissivity of a material at different spectral lengths. + + + The emissivity of a material can vary with the spectral wave length. + The vectors diffuseEmissivity and waveLength must have the same size to be valid. + The data should be linearly interpolated. + + + + + + + + + + + Wave length in [m] + + + + + Diffuse emissivity of the material + + + + + + + + + + + + + Emtpy element + + + Base type for string nodes (including external data + attributes) + + + + + + + + + + + + + + + + + Energy Carriers + + + + + + + + + + + + + + + + + + + + Energy carrier (fuel) configuration + + + + + + + + + + + + + + + + + + + + engineAnalysisType + + + + + + + + + + + + + Thrust at takeoff + + + + + Fan pressure ratio at takeoff + + + + + + Bypass ratio at takeoff + + + + + overall pressure ratio at takeoff + + + + + + Maximum rotations per second, shaft 1 + + + + + + Maximum rotations per second, shaft 2 + + + + + + Design tip relative mach number (FAN) + + + + + + DryMass of engine + + + + + + + + + + + + + + Definition of global geometry parameters of the engine + fan. + + + + + + + + + + + + + Inner radius of the fan. + + + + + Outer radius of the fan. + + + + + + + + + + + + + Definition of the global engine geometry. + + + + All engine geometry definitions refer to the engine + coordinate system. The engine coordinate system has its orgine + in the middle of the fan plan. The positive x-axis is heading to + the rear, the positive z-axis to the top and the y-axis + according to the right hand rule. + + + + + + + + + + + length of engine + + + + + diameter of engine + + + + + dProp + + + + + Chordlength of a fan blade + + + + + + + + + + + + + + + + + engineGlobalType + + + EngineGlobal type, containing global engine data + + + + + + + + + + + Concept of engine + + + + + + + + + + + + + + + Year of first certification + + + + + + Rotation direction of the engine if looking at + it from the front, i.e. from propeller/fan to exhaust + + + + + + + + + + + + + + Hub to tip ratio + + + + + Number of rotor blades of fan + + + + + + Number of outlet guiding vanes + + + + + + Rotor stator spacing (relative to chordlength) + + + + + + + + + + + + + + List of all engine mounts. + + + + + + + + + + + + + + + + + + + + + + Definition of one engine mount. + + + + + + + + + + + + + Name of the engine mount. + + + + + Description of the engine mount. + + + + + + position of the engine mount referring to the + engine coordinate system. + + + + + + UID of the engine mount. + + + + + + + + + + + + Engine nacelle + + + + The engine nacelle is part of an engine. + It allows to define the outer geometry of the following engine components: + + Fan cowl + Core cowl + Center cowl + + + All geometric values refer to the fan position. + + + The common use case for this definition includes bypass engines. + In the case of non-bypass engines, the core cowl should be omitted. + + + + + + + + + + + + + + + Fan cowl + + + + + Core cowl + + + + + + + + + + + + + + + enginePerformanceMapsType + + + + + + + + + + + + + + + + + + + + + + enginePerformanceMapType + + + EnginePerformanceMap type, containing a performance map + with engine data + + + + + + + + + + + + + + Flight Level + + + + + Mach number + + + + + Absolute thrust [N] + + + + + Fuel mass flow + + + + + Speed at core engine nozzle + + + + + + Total temperature at core engine nozzle + + + + + + Mass flow through core engine nozzle + + + + + + Speed at bypass nozzle + + + + + Total temperature at bypass nozzle + + + + + + Mass flow through bypass nozzle + + + + + + Percent of n1Max, shaft 1 + + + + + Percent of n2Max, shaft 2 + + + + + Fan pressure ratio + + + + + Fan efficiency + + + + + Turbine entry total temperature + + + + + + Emission index Carbon Monoxide + + + + + + Emission index Nitrogen Oxide + + + + + + Emission index Sulfur Oxide + + + + + + Emission index Soot + + + + + Emission index unburned hydrocarbon + + + + + + air density at core outlet 8 + + + + + + air density at bypass outlet 18 + + + + + + area at core outlet + + + + + area at bypass outlet + + + + + + + + + + + + + + Engine references + + + EnginePositions type, containing a reference to the + used engines and their positions at the configuration + + + + + + + + + + + + + + + + + + + enginePositionType + + + EnginePosition type, containing data for a single + engine + + + + + + + + + + Name of the engine + + + + + Description of the engine + + + + + Reference to the used engine + + + + + + Component, to which the engine is mounted + + + + + + + + + + + + + + + + + Engine pylons + + + + + + + + + + + + + + + + + + + + + + Definition of one engine pylon. + + + + + + + + + + + + + Name of the engine pylon. + + + + + Description of the engine pylon. + + + + + + UID of the parent (normally wing or fuselage). + + + + + + + + + + + + UID of the engine pylon. + + + + + + + + + + + + + Rotors + + + + + + + + + + + + + + + + + + + + Propeller + + + + + + + + + + + + + + + + + + + + + + Definition of the engine spinner geometry. + + + + + + + + + + + + + Most forward x-position of the spinner. + + + + + + X-position of the spinner base. + + + + + + Radius of the spinner at the base position. + + + + + + + + + + + + + + Engines + + + Engines type, containing complete engine configurations + + + + + + + + + + + + + + + + + + + + engineType + + + Engine type, containing engine data. + + + + + + + + + + Name of engine + + + + + Description of engine + + + + + Scaling of engine take-off thrust + + + + + + + + + + + + + + + + + + + + + Environmental conditions + + + + Specification of environmental conditions + + + + + + + + + + + + Delta temperature with respect to the standard temperature of the selected atmosphere [K] + + + + + + + + + + + + + + etaIsoLineType + + + Iso line described by point of the same eta coordinate. + Can be either segment or component segment coordinates. + + + + + + + + + + Relative spanwise position. Eta refers to the segment or componentSegment depending on the referenced uID. + + + + + This reference uID determines the reference coordinate system. + If it points to a segment, then the eta value is considered to be in segment + eta coordinate; if it points to a componentSegment, + then componentSegment eta coordinate is used. + + + + + + + + + + + + + Point in eta and xsi coordinates + + + Point described by eta-xsi coordinates. + Can be either segment or component segment coordinates. + + + + + + + + + + Relative spanwise position. Eta refers to the segment or componentSegment depending on the referenced uID. + + + + + Relative chordwise position. Xsi refers to the segment or componentSegment depending on the referenced uID. + + + + + This reference uID determines the reference coordinate system. + If it points to a segment, then the eta-xsi values are considered to be in segment + eta-xsi coordinates; if it points to a componentSegment, + then componentSegment eta-xsi coordinates are used. + + + + + + + + + + + + + Relative height at eta, xsi position + + + Point described by eta-xsi and a relative height coordinate. + Can be either segment or component segment coordinates. + If relHeight is not given, the point has no offset from the eta-xsi plane + + + + + + + + + + Relative spanwise position. Eta refers to the segment or componentSegment depending on the referenced uID. + + + + + Relative chordwise position. Xsi refers to the segment or componentSegment depending on the referenced uID. + + + + + Relative height position. + relHeight is relative to the local airfoil thickness. + + + + + This reference uID determines the reference coordinate system. + If it points to a segment, then the eta-xsi values are considered to be in segment + eta-xsi coordinates; if it points to a componentSegment, + then componentSegment eta-xsi coordinates are used. + + + + + + + + + + + + + fatigueBehaviourType + + + + + + + + + + + + + Fatigue law, stress based Brown Miller approach [N/m^2] + + + + + + + + + + + + + fatigueStressBasedBrownMillerType + + + + + + + + + + + + + Parameter sigma_f [N/m^2] + + + + + Parameter b [-] + + + + + Parameter epsilon_f [-] + + + + + Parameter c [-] + + + + + + + + + + + + + fleetType + + + Each fleet can be divided into sub fleet groups + + + + + + + + + + Name of fleet + + + + + Description of the fleet + + + + + Description of sub-fleets. + + + + + + + + + + + + + + flightAnalysisType + + + + + + + + + + + + + + + + + + + + + + + Flight dynamics + + + + + + + + + + + + + + + + + + + + + + + + Linear model parameters + + + + + + + + + + + + + + + + + + + + + + + + + + Trim result + + + + + + + + + + + Mach number + + + + + + + True airspeed + + + + + + + Angle of attack + + + + + + + Altitude + + + + + + + + + + + + + + Flight envelope speed + + + + Specification of the V-speed + + + + + + + + + + + + + Vector with altitudes + + + + + + + Vector with True Airspeeds + + + + + + + + + + + + + + Flight Envelopes + + + + Specification of flight envelopes + + + + + + + + + + + + + + + + + + + + Flight Envelope + + + + Specification of a flight envelope + + + + + + + + + + + + Offset from temperature of the atmospheric model [K] + + + + + + + + + + + + + + + Flight load cases + + + + + + + + + + + + + + + + + + + + + + Load conditions + + + Inertia load conditions acting on the aircraft + + + + + + + + + + + Description + + + + + + + Safety factor applied on the loads + + + + + + + + Rotational rates around centre of gravity + + + + + + + Enumeration flag stating the typ of the load + case (i.e. limit or ultimate loads) + + + + + + + + + + + + + Angle of sideslip [deg] + + + + + + + Angle of attack [deg] + + + + + + + + + + + + + + + + Flight loads + + + Loads resulting from the load case analysis + + + + + + + + + + + + + + + + + + + + + Flight path + + + Definition of a flight path by points of longitude, latitude and a descriptive waypoint code. + + + + + + + + + + Vector of waypoint codes. If waypoint codes are not available put empty items into the waypoint string + + + + + Vector of waypoint latitude values in [deg] + + + + + Vector of waypoint longitude values in [deg] + + + + + Indicates the type of the way point. + + + + + + + + + + + + + + + + + + + + Performance cases + + + List of performance cases + + + + + + + + + + + + + + + + + + + Performance case + + + + + + + + + + + + + + Name + + + + + + + Description + + + + + + + UID of flight performance requirement + + + + + + + + + + + + + + + + + + + + + + + Results of the landing analysis + + + + + + + + + + + + + Determined landing distance. + + + + + + Determined ground phase distance. + + + + + + + + + + + + + + + Level flight + + + + + + + + + + + + + + Specific excess power + + + + + + + + + + + + + Flight performance requirements + + + Contains a list of flight performance requirements + + + + + + + + + + + + + + + + + + + + Flight performance requirement + + + + + + + + + + + + + Name of the performance case + + + + + Description of the performance case + + + + + + Reference to the considered weightAndBalance case + + + + + The UID of the mission to be flown + + + + + List of point performance uIDs constraining the mission + + + + + + + + + + + + + + + + Results of the take-off analysis + + + + + + + + + + + + + Main element containing the results for + take-off calculations optimized for min-imum liftoff speed + VLOFmin. + + + + + Main element containing the results for + take-off calculations optimized for min-imum safety speed V2min. + + + + + + + + + + + + + + Turn + + + + + + + + + + + + + ... + + + + + ... + + + + + + + + + + + + + Flight Cases + + + + + + + + + + + + + + + + + + + + + + + + flightPointType + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Flights + + + Flighs type, containing all flight definitions + + + + + + + + + + + + + + + + + + + + Flight systems + + + + + + + + + + + + + + + + + + + + + + flightType + + + Flight type, containing data of a scheduled flight + + + + + + + + + + MissionUID for the flights mission definition + + + + + ModelUID of the aircraft appointed to perform the flight + + + + + Departure day of the flight + + + + + Time of departure - the time is defined as SOBT (Scheduled Off-Block Time) / STD (Scheduled Time of Departure) + + + + + Arrival day of the flight + + + + + Time of arrival - the time is defined as SIBT (Scheduled In-Block Time) / STA (Scheduled Time of Arrival) + + + + + Reference to the operating airline of a flight + + + + + + + + + + + + + + + floorPanelsType + + + FloorPanels type, containing floor panel definitions + + + + + + + + + + + + + + + + + + + + floorPanelAssemblyPositionType + + + FloorPanelAssemblyPosition type, containing a floor + panel assembly position + + + + + + + + + + x coordinate of the begin of the floor panel + (absolute value) + + + + + x coordinate of the end of the floor panel + (absolute value) + + + + + UID of the first long. floor beam to be + connected to the floor panel + + + + + UID of the second long. floor beam to be + connected to the floor panel + + + + + UID of structural sheet element used for the + floor panel + + + + + + + + + + + + + + + Flying qualities + + + Provides a list of flying qualities cases + + + + + + + + + + + + + + + + + + + + Flying qualities case + + + + + + + + + + + + + Name + + + + + Description + + + + + Aircraft Class; Class 1 small light aircraft; + Class 2 medium weight aircraft, low to medium maneuverability; + Class 3 large, heavy aircraft, low to medium maneuverability; + Class 4 high maneuverability aircraft + + + + + Flight Phase Category; Category A Non-terminal + flight phases requiring maneuvering, precision tracking, or + precise flight-path control (e.g. air-to-air combat, terrain + following). Category B Non-terminal Flight Phases with gradual + maneuvers and without precision tracking, although accurate + flight-path control may be required (e.g. climb, cruise). + Category C Terminal Flight Phases are normally accomplished + using gradual maneuvers and usually require accurate flight-path + control (takeoff, approach and landing). + + + + + main element containing longitudinal transfer + functions + + + + + main element containing lateral directional + transfer functions + + + + + main element containing characteristic + parameters of the handling qualities criteria + + + + + + main element containing handling qualities + ratings + + + + + + + + + + + + + + fqCharParametersType + + + + + + + + + + + + + static margin [-] + + + + + main element containing characteristic + parameter of phugoid damping + + + + + main element containing characteristic + parameters of short period mode criteria + + + + + main element containing characteristic + parameters of roll oscillation criterion + + + + + coupling of roll and spiral mode: normal = no + coupling of roll and spiral mode coupled = coupling of roll and + spiral mode + + + + + main element containing characteristic + parameters of lateral eigenvalues + + + + + main element containing characteristic + parameters of effective roll time constant criterion + + + + + + main element containing characteristic + parameters of roll performance criterion + + + + + + + + + + + + + fqEiglatType + + + + + + + + + + + + + natural frequency of dutch roll mode [rad/s] + + + + + + damping of dutch roll mode [-] + + + + + + roll time constant [s] + + + + + time to double of spiral mode [s] + + + + + + ratio of bank to sideslip angle [-] + + + + + + natural frequency of coupled rollspiral motion + [rad/s] + + + + + damping ratio of coupled roll-spiral motion + + + + + + product of roll-spiral damping and natural + frequency [rad/s] + + + + + handling qualities level of roll time constant + + + + + + handling qualities level of roll spiral mode + + + + + + + + + + + + + + fqLateralType + + + + + + + + + + + + + numerator of transfer function roll control + surface deflection to bank angle + + + + + numerator of transfer function roll control + surface deflection to yaw rate + + + + + numerator of transfer function roll control + surface deflection to sideslip angle + + + + + numerator of transfer function roll control + surface deflection to bank angle of reduced 4th order system + + + + + + numerator of transfer function roll control + surface deflection to sideslip angle of reduced 4th order system + + + + + + numerator of transfer function yaw control + surface deflection to yaw rate + + + + + numerator of transfer function yaw control + surface deflection to sideslip angle + + + + + numerator of transfer function roll stick + input to roll rate + + + + + numerator of transfer function roll stick + input to yaw rate + + + + + numerator of transfer function roll stick + input to bank angle + + + + + numerator of transfer function roll stick + input to sideslip angle + + + + + numerator of transfer function pedal input to + roll rate + + + + + numerator of transfer function pedal input to + yaw rate + + + + + numerator of transfer function pedal input to + bank angle + + + + + numerator of transfer function pedal input to + sideslip angle + + + + + denominator of lateral motion + + + + + + denominator of lateral motion of reduced 4th + order system + + + + + + + + + + + + + fqLongitudinalType + + + + + + + + + + + + + numerator of transfer function pitch stick + input to pitch rate + + + + + numerator of transfer function pitch control + surface deflection to pitch angle + + + + + numerator of transfer function pitch stick + input to pitch angle + + + + + numerator of transfer function pitch stick + input to angle of attack + + + + + numerator of transfer function pitch stick + input to vertical load factor + + + + + denominator of longitudinal motion + + + + + + + + + + + + + + fqPhugoidType + + + + + + + + + + + + + damping ratio of phugoid mode [-] + + + + + + time to double amplitude of unstable phugoid + mode [s] + + + + + + + + + + + + + fqRatingsType + + + + + + + + + + + + + handling qualities level of phugoid damping + + + + + + handling qualities level of C* criterion + + + + + + main element containing handling qualities + levels of short period mode + + + + + main element containing handling qualities + levels of roll oscillation criterion + + + + + main element containing handling qualities + levels of lateral eigenvalues + + + + + handling qualities level of effective roll + time constant + + + + + handling qualities level of roll performance + + + + + + + + + + + + + + fqRollPerfType + + + + + + + + + + + + + time to reach critical bank angle [s] + + + + + + critical bank angle that has to be reached + [deg] + + + + + + + + + + + + + fqRoloscType + + + + + + + + + + + + + ratio of oscillatory component of the roll + rate to the average roll rate [-] + + + + + phase angle of dutch roll oscillation in + sideslip [deg] + + + + + phase angle between roll rate and sideslip in + dutch roll mode [deg] + + + + + ratio of first minimum roll rate to first + maximum [-] + + + + + handling qualities level of ratio of + oscillatory component of roll rate to average roll rate + + + + + + + + + + + + + + fqShortPeriodType + + + + + + + + + + + + + steady state normal acceleration change with + angle of attack [g/rad] + + + + + short period natural frequency of reduced + order system [rad/s] + + + + + short period damping ratio of reduced order + system [-] + + + + + equivalent pitch time delay of reduced order + system [s] + + + + + handling qualities level of CAP criterion + + + + + + + + + + + + + + fqTreffType + + + + + + + + + + + + + effective roll time constant [s] + + + + + + time where tangent of bank angle step response + is placed [s] + + + + + + + + + + + + + framesAssemblyType + + + FramesAssembly type, containing frames assembly + + + + + + + + + + + + + + + + + + + + frameType + + + frame type, containing frame definition (V1.5+) + + + + + + + + + + + + + + + + + + + + + freePathType + + + + + + + + + + + + + + + + + + + + + + + Frustum + + + + + + + + + + Upper radius [m] + + + + + Upper radius [m] + + + + + Height [m] + + + + + + + + + + + + + mass + + + + + + + + + + + + + + + + + + + + + + Fuel Mass Fraction + + + Describing the mass fraction considered for a mission segment sequence + + + + + + + + + + Reference to the segment from which the fuel fraction should be considered + + + + + Reference to the segment to which the fuel fraction should be considered + + + + + Float value of the mass fraction defined as + fraction = m_end / m_start + + + + + + + + + + + + + Definition of different volumes of the fuel tank. + + + + + + + + + + + + + + Theoretical volume if material thicknesses + (ribs, spars, skins, stringers) and systems (fuel pumps, + pipes...) are neglected. + + + + + + + Usable fuel volume aircraft operations. + + + + + + Total real fuel tank volume. + + + + + + + + Factor between the usalbe fuel volume and + the real fuel volume. + + + + + Factor between the real fuel volume and the + theoretical optimum fuel volume. + + + + + + + + + + + + + + + fuselageAeroPerformanceType + + + fuselageAeroPerformance type, containing performance + maps with aerodynamic data of a fuselage. + + + + + + + + + + Reference to the uID of the analysed fuselage + + + + + + References used for the calculation of the + force and moment coefficients of the fuselage (in the fuselage + axis system!) + + + + + Calculated aerodynamic performance maps of the + fuselage + + + + + + + + + + + + + fuselageCutOutsType + + + fuselageCutOuts type, containing fuselage cutouts + + + + + + + + + + + + + + + + + + + + fuselageCutOutType + + + fuselageCutOut type, containing a fuselage cutout + definition + + + + + + + + + + Name of the cutout + + + + + Description of the cutout + + + + + X position of the cutout center point + + + + + + Y offset of the cutout reference point + + + + + + Z offset of the cutout reference point + + + + + + Angle in degrees of the vector pointing from + the cutout reference point to the cutout center point, measured + relative to the direction of the fuselage z axis. + + + + + + Coordinates of the unit vector defining the + direction of extrusion + + + + + Coordinates of the unit vector defining the + y-axis of the local cutout coordinate system. Must be normal to + the orientationVector. + + + + + This value is used to define the width of the + cutout + + + + + This value is used to define the height of the + cutout + + + + + This value is used to define the width of the + cutout + + + + + This value is used to define the height of the + cutout + + + + + Fillet radius of the cut element (absolute + value) + + + + + Cutout type. Determines the type of the cutout + and how it is treated by the tools. Possible values: + ("window"|"door"|"ramp") + + + + + + + + + + + + + + + + + + + + + + + + + + fuselageElementsType + + + FuselageElements type, containing the elements of a + fuselage section + + + + + + + + + + + + + + + + + + + fuselageElementType + + + FuselageElement type, containing fuselage element data + + + + + + + + + + + Name of fuselage element + + + + + Description of fuselage element + + + + + + Reference to a fuselage profile + + + + + + + + + + + + + + + + List of fuel tanks + + + + + + + + + + + + + The fuselage fuel tank geometry is defined by a link to a fuselage geometry compartment. +The fuel tank volume type should also be used for the wing fuel tank + + + + + + + + + + + + + + fuselageProfilesType + + + FuselageProfiles type, containing fuselage profile + geometries. See profileGeometryType for further documentation + + + + + + + + + + + + + + + + + + + + fuselagesAeroPerformanceType + + + fuselagesAeroPerformance type, containing + fuselagesAeroPerformance + + + + + + + + + + + + + + + + + + + fuselageSectionsType + + + FuselageSections type, containing fuselage sections + + + + + + + + + + + + + + + + + + + + fuselageSectionType + + + FuselageSection type, containing fusleage section and + element data + + + + + + + + + + Name of fuselage section + + + + + Description of fuselage section + + + + + + + + + + + + + + + + + fuselageSegmentsType + + + FuselageSegments type, containing fuselage segment + definitions (from sections and elements) + + + + + + + + + + + + + + + + + + + fuselageSegmentType + + + FuselageSegment type, containing data of a fuselage + segment + + + + + + + + + + Name of fuselage segment + + + + + Description of fuselage segment + + + + + + Reference to element from which the segment + shall start + + + + + Reference to element at which the segment + shall end + + + + + Optional and additional guidecurves to shape + the outer geometry. + + + + + + + + + + + + + + Structural mounts + + + + + + + + + + + + + + + + + + + fuselageStructureType + + + FuselageStructure type, containing data of the fuselage's + structure + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Fuselages + + + Fuselages type, containing the fuselages of the + configuration + + + + + + + + + + + + + + + + + + + fuselageType + + + + Fuselage type, containing all data related to a + fuselage + + + + + + + + + + + + + + + Name of fuselage + + + + + + + Description of fuselage + + + + + + + UID of part to which the fuselage is + mounted (if any) + + + + + + + + + + + + + + + + + + + + + + + + + Galley elements + + + Galley element collection type + + + + + + + + + + Galley element for use in the decks + + + + + + + + + + + + + Galley element + + + Galley element type, containing the base elements of the cabin + + + + + + + + + + Number of trolleys + + + + + + + + + + + + + Galleys + + + Galley instance collection type. + + + + + + + + + + Galley + + + + + + + + + + + + + Gas turbines + + + + + + + + + + + + + + + + + + + GasTurbine + + + + + + + + + + + + + + + Gear boxes + + + + + + + + + + + + + + + + + + + Gear box + + + + + + + + + + + + + + + This type contains a list of gears and their deflection + vectors + + + + + 0. General overview + + In this type, a list of gears is defined. + + + + + + 1. + <gear> + (mandatory) + + + One of these nodes per deflected gear is required + here. + + + + + + + + + + + + + + + + + + + + + + This type contains a vector of deflection values for a + single gear + + + + + 0. General overview + + In this type, a vector of deflections of a single + gear is specified. + + + + + 1. + <gearUID> + (mandatory) + + + A reference to a gear from the aircraft model + + + + + + 2. + <controlParameters> + (mandatory) + + + A vector of control parameters of the selected + gear + + + + + + + + + + + + + Reference to a gear + + + + + Control parameters of the gear + + + + + + + + + + + + + + stringerFramePositionType + + + stringerFramePosition type, containing individual + stringer / frame position definition (CPACS V2.1+) + + + + + + + + + + + + + + + + + + + + + Continuity definition for profile extrusion: + 0= C0 (allows sharp edges, default), 2= C2 (defines curvature + continuity) + + + + + + + + + + + + + Definition of interpolation between different + profiles: 0= no interpolation 1= interpolation of structural + profile + + + + + + + + + + + + + + + + + + + + + + generalStructuralMembersAssemblyType + + + generalStructuralMembersAssembly type, containing + structural member assemblies + + + + + + + + + + + + + + + + + + + generalStructuralMemberType + + + + + + + + + + + + + + + + + + + + + + + + Generators + + + + + + + + + + + + + + + + + + + Generator + + + + + + + + + + + + + + + Generic components + + + + + + + + + + + + + + + + + + + genericCostType + + + + + + + + + + + + + + + + + + + + + + + + Generic floor elements + + + Generic floor element collection type + + + + + + + + + + Generic floor element for use in the decks + + + + + + + + + + + + + Generic floor modules + + + Generic floor module instance collection type. + + + + + + + + + + Generic floor module + + + + + + + + + + + + + Global design parameters + + + + + + + + + + + Inner radius of the cylinder + + + + + Inner length of the cylinder + + + + + + + + + + + + + + + Generic fuel tank + + + + + + + + + + + + + + + + + + + + + + Cryogenic tank + + + + + + + + + + Name + + + + + + Description + + + + + + + + + + Burst pressure + + + + + + + + + + + + + + genericGeometricComponentType + + + + In some cases additional geometric components need to + be linked to a CPACS, but these components are not yet handled by + CPACS explicitly. For example, a belly fairing and/or external + tanks. + A generic geometric component may be applied to include + such a geometry from an external file (preferably STEP) in the + context of the overall aircraft. + + + + + + + + + + + + + + Name of genericGeometricComponent + + + + + + Description of genericGeometricComponent + + + + + + UID of part to which the component is mounted + (if any) + + + + + + + + + + + + + + + + + Generic geometric components + + + + + + + + + + + + + + + + + + + + + + Generic geometry component + + + + + + + + + + + + + + + + + + + + + + + Mass description + + + + + + + + parentUID + not set + + + parentUID + set + + + + + location + without + refType + + global + local + + + + location + with + refType="absLocal" + + global + local + + + + location + with + refType="absGlobal" + + global + global + + + + Note: + The combination of + location + with + refType="absLocal" + and no + parentUID + is global, because the local coordinate system to which the + location + is referring to via + refType + equals the global coordinate system. + + + + + ... + + + ... + + + ... + + + ... + + + ]]> + + + + + ... + + + ... + + + ... + + + ... + + + ]]> + + + + + ... + + + ... + + + ... + + + ... + + + ]]> + + + + wingUID + + ... + + + ... + + + ... + + + ... + + + ]]> + + + + wingUID + + ... + + + ... + + + ... + + + ... + + + ]]> + + + + wingUID + + ... + + + ... + + + ... + + + ... + + + ]]> + + + + + + + + + + + + Name + + + + + Description + + + + + UID of the component which serves as parent element, i.e. whose coordinate system is to be used as a reference for the mass properties (CoG location, orientation and massInertia). Thus, two cases can occur: (1) + it is set: local coordinate system of the parent; (2) it is not set: global CPACS coordinate system. + + + + + + UID of the geometric description of the component. + + + + + + Mass [kg] + + + + + Mass location. + If the optional refType attribute is set, it explicitly specifies whether the location of the mass refers to the global CPACS coordinate system (absGobal) or the local coordinate system of the parent element (absLocal, given by the CPACS hierarchy OR by parentUID). + If it is not set, the global CPACS coordinate system is considered as default. + To ensure consistency, the same settings apply as well to orientation and massInertia. + + + + + + Orientation. The reference coordinate system (absGlobal or absLocal) is identical to location. + + + + + Mass inertia. The reference coordinate system (absGlobal or absLocal) is identical to location. + + + + + + + + + + + + + + genericSystemsType + + + Node for geometrical layout of system components + based on simple geometric shapes + + + + + + + + + + + + + + + + + + + Generic system + + + + + + + + + + Name + + + + + Description + + + + + + + + + + + + + + + geographicPointConstraintType + + + Geographic point constraint, containing a longitude, latitude, altitude data triplet. + + + + + + + + + + + Longitude coordinate 0-360 + + + + + + + + + + + + Latitude coordinate 0-360 + + + + + + + + + + + + Altitude in meters + + + + + + + + + + + + + + + + + + + geographicPointType + + + Geographic point type, containing a longitude, latitude, altitude data triplet. + + + + + + + + + + Longitude coordinate 0-360 + + + + + Latitude coordinate 0-360 + + + + + Altitude in meters + + + + + + + + + + + + + + airfoilAeroPerformanceType + + + airfoilAeroPerformance type, containing performance maps + with aerodynamic data of an airfoil. + + + + + + + + + + References used for the calculation of the + force and moment coefficients + + + + + Calculated aerodynamic performance maps of the + full configuration + + + + + + + + + + + + + globalBeamPropertiesType + + + globalBeamPropertiesType, containing the global beam + properties such as EA, EI, mass + + + + + + + + + + + + + + + + + + + + + + + + + + + Flight point + + + + + + + + + + + + + + + + + + + + Mach number + + + + + + + Calibrated air speed + + + + + + + True air speed + + + + + + + + + + + + + + + + + Performance Cases + + + + Specification of performance cases required for the performance evaluation of air vehicles (aircraft, rotorcraft, etc.). + + The information in this node is + generally + applicable to any kind of vehicle. + Vehicle-specific + information is provided through the performanceRequirements node found under: + /cpacs/vehicles/../model/performanceCases + . + + + + + + + + + + + + + + + + + + + + + + Ground load Cases + + + + + + + + + + + + + + + + + + + + + + guideCurveProfileGeometryType + + + + A guide curve profile is defined by a profile name, an + optional description and a 3-dimensional relative pointlist with + all three coordinates mandatory. For typical profiles, one of + the coordinate vectors contains only "0" entries. All point + coordinates are transferred to the global coordinate system. + First and last point may, but need not to, be identical. + + The points have to be ordered in a mathematical + positive sense. + A profile can be symmetric. In that case the profile + is interpreted as being not closed and will be closed by + mirroring it on the symmetry plane. + Curves have to go continuously over the whole wing or + fuselage + Connection of guide curves from segment to segment + + + + + + + + Please note, currently it is not possible to apply any + means of class based transformation in the description. However, + this may be an addition for the future. + + + + + + + + + + + Name of profile + + + + + Description of profile + + + + + + + + + + + + + + + + guideCurveProfilesType + + + Guide Curve Profiles type. This type is used to + describe guide curves that enable designers to create a geometry + that deviates from a standard loft. + + + + + + + + + + + + + + + + + + + + Guide Curves Type + + + Guide Curve type. This type is used to describe guide + curves that enable designers to create a geometry that deviates + from a standard loft. + + + + + + + + + + + + + + + + + + + Guide Curve Type + + + + A guide curve may be used to alter the shape of the + outer geometry and "guide" the loft. + The guide curve profiles are defined in the guideCurveProfileGeometryType. + Their use on wing and fuselage components is illustrated in the image below. + + + + + + + + + + + + + + + Name of guide curve + + + + + Description of guide curve + + + + + Reference to a guide curve profile + + + + + + For the first segment fromGuideCurveUID is not + a valid entry! For the first guideCurve + fromRelativeCircumference must be applied! fromGuideCurveUID is + exclusive. + + + + + + Reference to the previous guide curve from + which this guide curve shall start. + + + + + + Continuity definition for geometry + generation. Possible options: C0, C1 from previous, C2 from + previous, C1 to previous, C2 to previous + + + + + + + + + + + + + + + + + + + Reference to the relative circumference + position from which the guide curve shall start. Valid values + are in the interval -1.0...1.0. + + + + + + Tangent at first point + + + + + + + + The relative circumference + position at which the guide curve shall end. Valid values + are in the interval -1,..,1. + + + + + + Tangent at last point + + + + + + Local direction along which the relative x-coordinates of + the guide curve points are defined. For the wing the default is + the wing's local x-axis, for the fuselage its the fuselage's local z-axis. + + + + + + + + + + + + + + + CPACS header + + + Header type, containing CPACS dataset description + + + + + + + + + + + Name of CPACS dataset + + + + + Description of CPACS dataset + + + + + + Version of initial CPACS dataset according to the Semantic Versioning 2.0.0 standard. + + + + + + DEPRECATED: Should only be set to allow TiGL to open the file until TiGL is adopted accordingly. + Will be replaced by the cpacsVersion element in versionInfos. + + + + + + + + + + + + + + + Heat exchangers + + + + + + + + + + + + + + + + + + + Heat exchanger + + + + + + + + + + + + + + + Heat flow + + + + + + + + + + + Heat flow value + + + + + + + + + + + + + + + + + + Heat flow + + + + + + + + + + + Heat flow value + + + + + + + + + + + + + + + + + + hingeMomentsMapType + + + hingeMomentsMap type, containing a hinge moments map + with aerodynamic data. Array order is: angleOfAttack min->max + then angleOfSideslip then reynoldsNumber then machNumber. + All coefficients in the aeroperformanceMap relate to + the CPACS coordinate system. See documentation of the + CPACS-Element for further information. + + + + + + + + + + Name of the AeroPerformanceMap. + + + + + + Description of the AeroPerformanceMap. + + + + + + Mach number + + + + + Reynolds Number + + + + + Sideslip angle + + + + + Angle of attack + + + + + + + + + + + + + + htpFwdInterfaceDefType + + + Definition of the interface of forward HTP attachment + + + + + + + + + + Definition of the forward HTP attachment + interface + + + + relative width of reinforcement at fwd HTP + attachment, between 0.0 and 1.0 + + + + + relative width of plate at fwd HTP attachment + (only applicable for Type1 model), between 0.0 and 1.0, smaller + than htpPlateWidth + + + + + UID of panel element at HTP forward attachment + in x-direction (shell elements) + + + + + UID of panel element at HTP forward attachment + in z-direction (shell elements) + + + + + UID of reinforcements for panel element at HTP + forward attachment in z-direction (beam elements) + + + + + + UID of the element to fix HTP to fuselage + (beam elements) + + + + + + + + + + + + + + htpInterfaceDefType + + + Definition of the interface of HTP + + + + + + + + + Definition of the HTP interface + + + + + UID of the fuselage frame at the forward HTP + attachment + + + + + + UID of the fuselage frame at the backward HTP + attachment + + + + + + maximum HTP deflection (nose up in + degrees) + + + + + + maximum HTP deflection (nose down in + degrees) + + + + + + angle of the reinforcements at backward HTP + attachment + (in degrees) + + + + + + Defines area (absolute) in x-direction around + htpFrame2UID where the HTP attachmentpoint has correct position + ==> check and potentially warning message + + + + + Defines area (absolute) in y-direction around + the + outer edge of htpFrame2UID where the HTP attachmentpoint has correct + y-position ==> check and potentially warning + message + + + + + + Defines allowed z-position for rear HTP + attachment + relative to total frame height ==> check and potentially warning + message ==> check and potentially warning + message + + + + + + Definition of HTP structural + elements + + + + + + Definition of HTP forward attachment to + structure + + + + + + + + + + + + + + + htpStructElemDefType + + + definition of structural elements in HTP attachment + + + + + + + + + + Definition of tailplane attachment area + (Standard Configuration) + + + + UID of structural element for HTP front + crossbeams + + + + + UID of structural element for HTP rear + crossbeams + + + + + UID of structural element for HTP diagonal + beams + + + + + UID of structural element for HTP side beams + + + + + + UID of structural element for upper HTP cutout + reinforcement beams, also used for lower cutout reinforcement, + when not explicitly defined + + + + + UID of structural element for lower HTP cutout + reinforcement beams (optional) + + + + + + + + + + + + + + Skin Layers + + + + + + + + + + + + + + + + + + + + + + + Structure + + + + + + + + + + + + + + + + + + + + + + + + Hulls + + + + + + + + + + + + + + + + + + + Hulls + + + + + + + + + + Name + + + + + + Description + + + + + + + + + + + + + + + + + + + + indirectOperatingCostType + + + + + + + + + + + + + + + + + + + + + + Individual system categories + + + + + + + + Generic + + + + + + + + + + + integerBaseType + + + Base type for integer nodes (including external data + attributes) + + + + + + + + + + + + + + + + + + + List of fuselage fuel tanks integrated in compartments. + + + + + + + + + + + + + The integral fuel tank geometry is defined by a link to a fuselage geometry compartment. +The fuel tank volume type should also be used for the wing fuel tank + + + + + + + + + + + + + interConnectionStrutAttachmentType + + + + + + + + + + + + + Definition of the position of the attachment + joint in relative coordinates. + + + + + Material settings of the attachment. + + + + + + + + + + + + + + interconnectionStrutsType + + + + + + + + + + + + + Definition of one interconnection strut. + + + + + + + + + + + + + + interconnectionStrutType + + + + + + + + + + + + + uID of control surface where this flap is + attached to by the interconnection strut. + + + + + Material settings of the strut (if strut is + modeled as a simple strut). + + + + + Definition of the attachment on this control + surface. + + + + + Definition of the attachment on the other + control surface + + + + + Free path in positive (tensil) and negative + (compression) direction before interconnection strut blocks. + + + + + + + + + + + + + + + intercostalPositionType + + + intercostalPosition type, containing the position of intercostals + in DSS + + + + + + + + + + + + UID of the frame at which intercostal + starts + + + + + UID of the forward door frame + + + + + UID of the door + + + + + non-dimensional value ranging between 0 and 1 + + + + + + UID of profileBasedStructuralElement used for + intercostal + + + + + + + + + + + + + + IntercostalsAssemblyType + + + IntercostalsAssembly type, containing intercostal + definitions + + + + + + + + + + + + + + + + + + + structuralElementsConnectionsType + + + StructuralElementsConnections type, containing + connections between structural elements + + + + + + + + + + Flag for automatic generation of interface + definitions (draft version) + + + + + + + + + + + + + + + Isotensoid dome + + + + + + + + + + Radius of the fitting/smaller polar opening + + + + + + + + + + + + + Isotropic material properties + + + + Defines the material properties for an isotropic material. Note that the shear modulus G + is defined in terms of the elastic modulus E and the Poisson's ratio nu as: + + + + Specifying a value for all three properties E, G and nu therefore results in an overdetermined material definition and must be avoided. + + + + + + + + + + + + Young's modulus [N/m^2] + + + + + + + Shear modulus [N/m^2] + + + + + + + Poisson's ratio + + + + + + + Thermal expansion coefficient [1/K] + + + + + + + Thermal conductivity of the material in + [W/(m*K)] + + + + + + + Allowable stress for tension [N/m^2] + + + + + + + Allowable stress for compression [N/m^2] + + + + + + + Allowable stress for shear [N/m^2] + + + + + + + Allowable strain for tension + + + + + + + Allowable strain for compression + + + + + + + Allowable strain for shear + + + + + + + Yield strength, tension [N/m^2] + + + + + + + Yield strength, compression [N/m^2] + + + + + + + Plastification curves for isotropic + materials incl. element elimination + + + + + + + Optional knockdown factor for fatiuqe + (defaults to 1) + + + + + + + Fatigue behaviour of the material + + + + + + + Damage tolerance behaviour of the + material + + + + + + + + + + + + + + Landing gear base + + + + Base type for landing gears (i.e. nose gear, main gear and skid gear). + An example of a nose and main gear is shown below: + + + + + + + + + + + + + + Name + + + + + Description + + + + + UID of the parent component. If set, the position of the main strut is defined relative to the parent coordinate system. + + + + + + + + + Total length of landing gear, equals the distance from the middle of the bogie/axles to the axis of rotation of the pintle strut. Distance is measured while landing gear is fully extended and in airborne condition (i.e., if a spring is present, the totalLength includes the springDeflectionLength) + + + + + Static suspension travel means the positive distance between the total length in airborne condition and the reduced length due to compression on the ground. + + + + + Compressed suspension travel means the positive distance between the total length in airborne condition and the maximum reduced length due to maximum compression on the ground (e.g., landing shock). + + + + + + + Transformation with respect to the uppermost point of the main strut. From this point the landing gear is oriented in negative z-direction by default. + + + + + + + + + + + + + + + Braking function + + + + + Describes the braking state of the landing gear. + + + + + + + + + + Control parameter indicating that the brake is set + + + + + Control parameter indicating that the brake is released + + + + + + + + + + + + Assembly of landing gear components + + + + + Describes an assembly of the various landing gear components + + + + + + + + + + + + Main strut + + + + + + + + + + Drag strut (Assumption: one end of the strut will connect to the main strut and the other end will be given as endPoint) + + + + + + + + + + + + + + Landing gear control functions + + + + + A list of functions which can be addressed by the controlDistributor. + + + + + + + + + + Extension path + + + + + Steering path + + + + + Braking state + + + + + + + + + + + Landing gear control parameters + + + + Parameters of a landing gear control such as extraction or steering. + + + + + + + + + + + + Retraction angle of the main landing + gear. Equals a rotation around the + global z-axis in degrees. 0 = retraction + to the front; 90 = retraction to the + left; 180 = retraction to the rear; 270 + = retraction to the right. + + + + + + + + Distance of the center of rotation to the top of the main strut + for retracting and extending the landing gear. I.e., a value of + 0 means that the landing gear will rotate around the upper end + of the main strut during retraction. If this value is greater + than 0, the center of rotation is shifted by this value above + the main strut end point (translation along the main strut axis). + + + + + + + + + + + + + + Extension step + + + + + Describes a step with the extension path of the landing gear. Make sure to provide a least one step with stepType=extracted! + + + + + + + + + + Step type (retracted or extracted) + + + + + + + + + + + + Control parameter + + + + + Extension angle of the main strut [deg] + + + + + + + + + + + Extension path + + + + + Describes the extension path of the landing gears via a list of steps. + + + + + + + + + + Step within the extension path + + + + + + + + + + + + landingGearInterfaceDefinitionsType + + + CenterFuselage landing gear interface definitions + + + + + + + + + + + + + + + + + + + + + + + + + + keelbeamType + + + HighWingCenterFuselage / Keelbeam definition between + mainframe1 und mainframe2 + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + lateralPanelsType + + + HighWingCenterFuselage / lateral Panel definition + between mainframe1 und mainframe2 + + + + + + + + + + + + + + + + + + + + + + + + + + longFloorBeamConnectionType + + + HighWingCenterFuselage / Long. floor beam connection + + + + + + + + + + + + + + + + + + + + + centerFuselageMainFramesType + + + High wing main frame definition, containing mainframe + UIDs + + + + + + + + + + + + + + + + + + + + + + + pressureFloorType + + + High Wing Center Fuselage / pressure floor definition + between mainframe1 und mainframe2 + + + + + + + + + + + + + + + + + + + + + + + sideboxType + + + HighWingCenterFuselage / side box definition between + mainframe1 und mainframe2 + + + + + + + + + + + + + + + + + + + + + + Landing gear position safety margins + + + LandingGearPositionSafetyMargins type, containing the + safety margins of the gear due to its position + + + + + + + + + + Safety margin for landing gear x position + regarding tail clearance at takeoff pitch angle + + + + + + Safety margin for landing gear x position to + avoid tail dropping down during touchDown and ground maneuvering + + + + + + Safety margin for landing gear y position to + avoid wing tip dropping down during ground maneuvering + + + + + + Safety margin for landing gear y position + regarding wingtip or engine nacelle clearance at a certein roll + angle + + + + + + + + + + + + + Steering step + + + + + Describes a step with the steering path of the landing gear. + + + + + + + + + + Step type (centered, fullBackboard or fullStarboard) + + + + + + + + + + + + Control parameter + + + + + Steering angle [deg] + + + + + + + + + + + Steering path + + + + + Describes the steering path of the landing gears via a list of steps. + + + + + + + + + + Step within the steering path + + + + + + + + + + + + + Definition of the wing attachment + + + + + Definition of the wing attachment, if + attached to the wing. The definition + includes the position of the landing gear as + well as the information to which spars resp. + supportBeam the gear is attached. + + + + + + + + + + + + UID of the second spar, where the landing gear is attached to. Only used, if the landing gear is attached between two spars. + + + + + + UID of a set of ribs (ribDefinition) + + + + + Number of the rib in the rib set (ribDefinition) + + + + + + + + UID of the structural mount + + + + + + + + + + + + + + + Landing gears + + + Contains a list of landing gears. + + + + + + + + + + + + + + + + + + + Definition of the main landing gear support beam + position + + + Definition of the main landing gear support beam + position + + + + + + + + + + Relative chordwise coordinate (xsi) of the + inner end of the support beam. The eta + position of the inner end is defined by the eta position of the + wing root (=wing-fuselage attachment). + + + + + Relative spanwise coordinate (eta) of the + outer end of the support beam. The xsi + coordinate of the outer end is defined by the spar position + (first spar), where the support beam is attached to. + + + + + + + + + + + + + + Landing gears + + + LandingGear type, containing the definition of nose, + main and skid gears. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Lavatories + + + Lavatory instance collection type. + + + + + + + + + + Lavatory + + + + + + + + + + + + + Lavatory elements + + + Lavatory element collection type + + + + + + + + + + Lavatory element for use in the decks + + + + + + + + + + + + + Definition of the wings leading edge devices. + + + + Definition of the wings leading edge devices. + + + + + + + + + + + + + + + + + + + + Trailing edge device of the wing. + + + A leadingEdgeDevice (LED) is defined via its outerShape + relative to the componentSegment. The WingCutOut defines the area + of the skin that is removed by the LED. Structure is similar to + the wing structure. The mechanical links between the LED and the + parent are defined in tracks. The deflection path is described + in path. Additional actuators, that are not included into a + track, can be defined in actuators. + Leading and trailing edge are defined by the outer + shape of the wing segments, i.e. the trailing edge of a + trailingEdgeDevice is the trailing edge of the wing. This is also + valid for kinks that are present in the wing but not explicitly + modeled in the control surface. + The edges of the control surface within the wing are a + straight line in absolute coordinates! Hence, there needs to be a + straight connection between the eta-wise outer and inner points + of the edge that is within the wing in absolute coordinates. + + + + + + + + + + + Name of the leading edge device. + + + + + + Description of the leading edge device. + + + + + + UID of the parent of the LED. The parent is + the componentSegment, where it is attached to. + + + + + + + + + + + + + + + + + + + + + Optional definition of the airfoil inner shape of + leading edge devices (LED). + + + + All parameters are optional. For the definition of the + parameters, please refer to the picture below. Parameters from + the outer border default to the parameters of the inner border. + + + + + + + + + + + + + + + Relative height of the most forward point of + the LED's rear part, based on the airfoil height of the parent + at this position. Optional. + + + + + Relative chordwise position of the most + forward point of the LED's rear part, based on the chord of the + parent at this position. Optional. + + + + + + + + + + + + + Optional definition of the leading edge shape of + trailing edge devices (TED). + + + + All parameters are optional. For the definition of the + parameters, please refer to the picture below. Parameters from + the outer border default to the parameters of the inner border. + + + + + + + + + + + + + + + Relative height of the leading edge of the TED, + based on the airfoil height of the parent at this position. + Optional. + + + + + Relative chordwise upper skin position, of the + border, where the airfoil of the TED is equivalent of the + airfoil from the parent. Measured from the rear to the front (0 + = TED trailing edge; 1 = TED leading edge). Values form the + outer border default to the value of the inner border. Optional. + + + + + + Relative chordwise lower skin position, of the + border, where the airfoil of the TED is equivalent of the + airfoil from the parent. Measured from the rear to the front (0 + = TED trailing edge; 1 = TED leading edge). Values form the + outer border default to the value of the inner border. Optional. + + + + + + + + + + + + + + linerType + + + Liner type, containing liner data + + + + + + + + + + Type of liner + + + + + + + + + + + + + % of fan diameter + + + + + % of fan diameter + + + + + + + + + + + + + Link to file (Step, Iges or Stl) + + + Please provide a link to the additional file that shall + be loaded by the TIGL library. Furthermore it is necessary to + provide the format attribute so that the file type can be + identified. Several CAD formats provide multiple endings, and + hence, this measure seems necessary. + + + + + + + + + + + + + + + + + + + + + + + + + Definition of one fuel tank integrated in a fuselage compartment. + + + The definition of fuselage tanks is still preliminary. + Currently, there is no link to any structural elements + + + + + + + + + + + Name of the fuselage fuel tank. + + + + + + Description of the fuselage fuel tank. + + + + + + Link to the tank geometry defined by a compartment. + + + + + + + + + + + + + + + + + + + Load analysis + + + + + + + + + + + + + + + + + + + + + + + Load application points + + + + Multiple sets of scattered load application points can be defined. However, no specific information about the corresponding loads (e.g. whether aerodynamic or structural loads are involved) or mesh topologies are specified here, as such assumptions are tool-specific. + + + + + + + + + + + + + + + + + + + + Load application point set + + + + + A point set contains discrete spatial points at which loads are applied (e.g., aerodynamic or structural loads). A typical procedure in CPACS is as follows: + + + + + Reference a wing, fuselage or control surface by its + uID + using the + componentUID + node. + + + Define a reference axis through the above component with the + loadReferenceLine + element to specify where a load distribution shall be applied. + + + Compute the intersections with (e.g.) ribs of the referenced component (wing, fuselage or control surface) and write the results into + loadApplicationPoints + . This procedure results from common practice where the forces in structural analyses are typically introduced at structural elements such as ribs and spars. With respect to preliminary aircraft design a two-dimensional load distribution is preferred. However, an arbitrary distribution of the load application points is possible (without the intersection of structural elements with a reference axis in the previous step), for example to define discrete load distributions on the wing surface in streamwise and spanwise direction. + + + Specify the location and orientation of cut loads in the + cutLoadIntegrationPoints + element and the corresponding connectivity information in the + connectivities + node. + + + + + + + + + + + + + + + + + + UID of a wing, fuselage or control surface + + + + + + + Reference axis (line) for load distribution + + + + + + + List of points at which load vectors are + applied to + + + + + + + List of points at which cut loads are applied to + + + + + + + Specification of connectivity properties between points + + + + + + + + + + + + + + + dynamicAircraftModelCoordinatesType + + + + + + + + + + + + + + + + + + + + + + + + + loadBreakdownType + + + + + + + + + + + + + + + + + + + + + + + + + + Accelerations + + + Translational or rotational accelerations acting + on the aircraft + + + + + + + + + + + Rotational accelerations acting around aircraft centre of gravity [deg/s^2] + + + + + + + + + + + + + Gust definition + + + The coordinate system of the gust corresponds to the CPACS coordinate system. + + + + + + + + + + Parameters describing the shape of the gust + + + + + + + + + + + + + + + + + Angle between gust and vehicle [deg] (e.g., 0deg: from right to left; 90 deg: downwards; 180deg: from left to right; 270/-90deg: upwards) + + + + + + + Gust length: length of ramp or gradient distance of 1-cos gust + + + + + + + Gust velocity + + + + + + + + + + + + + + Load factors + + + + + + + + + + + + + + Load factor in x-direction + + + + + + + Load factor in y-direction + + + + + + + Load factor in z-direction + + + + + + + + + + + + + + Load case specification + + + Input values defining a load case + + + + + + + + + + + Environment + + + + + + + Altitude above sea level + + + + + + + Mach number + + + + + + + UID of the aerodynamic loads (aeroCase) + + + + + + + + Controller description. Note: Since there is no controller description in CPACS yet, the expected content of this string element has to be defined individually for each project. + + + + + + + + + + + UID referencing the mass state of aircraft for this load case + + + + + + + + + + + + + + Load cases + + + + + + + + + + + + + + + + + + + + + + + + + Load case superposition + + + List of uIDs referencing load cases that are superimposed to the current load case + + + + + + + + + + + + UID reference to another load case to be superimposed + + + + + + + + + + + + + + Load case + + + This node defines the load case + + + + + + + + + + + Name of the load case + + + + + + + Description of the load case + + + + + + + + + + + + + + + + + Load envelopes + + + The loads envelope is the results of the loadsAnalysis + and lists those loadcases that are limiting for the design + + + + + + + + + + + + + + + + + + + + Load envelope + + + List of load cases defining a load envelope + + + + + + + + + + + Name + + + + + Description + + + + + UID of the corresponding point set + + + + + + List of uIDs defining the loads envelope + + + + + + + + + + + + + loadReferenceAxisPointsType + + + + + + + + + + + + + + + + + + + + + + loadReferenceAxisPointType + + + + + + + + + + + + + + + + + + + Relative spanwise position. Eta refers to the segment or componentSegment depending on the referenced uID. + + + + + Relative chordwise position. Xsi refers to the segment or componentSegment depending on the referenced uID. + + + + + Relative height position. + relHeight is relative to the local airfoil thickness. + + + + + This reference uID determines the reference coordinate system. + If it points to a segment, then the eta-xsi values are considered to be in segment + eta-xsi coordinates; if it points to a componentSegment, + then componentSegment eta-xsi coordinates are used. + + + + + + + + + + + + + + Load sets + + + + A list of load sets + + + + + + + + + + + + + + + + + + + + Load set + + + A set of forces and moments + + + + + + + + + + + Description + + + + + + + UID of load application point set (analysis/global/loadApplicationPoints) + + + + + + + Force in x-direction [N] + + + + + + + Force in y-direction [N] + + + + + + + Force in z-direction [N] + + + + + + + Moment around x-axis [Nm] + + + + + + + Moment around y-axis [Nm] + + + + + + + Moment around z-axis [Nm] + + + + + + + Nodal displacement in x-direction [m] + + + + + + + Nodal displacement in y-direction [m] + + + + + + + Nodal displacement in z-direction [m] + + + + + + + Nodal rotation around x-axis [deg] + + + + + + + Nodal rotation around y-axis [deg] + + + + + + + Nodal rotation around z-axis [deg] + + + + + + + Load brake-down + + + + + + + + + + + + + + + Log entry + + + + + + + + + + Description of CPACS dataset + + + + + + Timestamp + + + + + + Creator (tool, person, etc.) + + + + + + + + + + + + + + logFloorBeamPositionType + + + longFloorBeamPosition type, containing individual + position definition + + + + + + + + + + UID of structural element + + + + + UID of crossbeam to which the long. beam is + attached + + + + + y position of long. beam + + + + + + Continuity definition for profile extrusion: + 0= C0 (allows sharp edges, default), 2= C2 (defines curvature + continuity) + + + + + + + + + + + + + Definition of interpolation between different + profiles: 0= no interpolation 1= interpolation of structural + profile + + + + + + + + + + + + + + + + + + + + + + longFloorBeamsAssemblyType + + + longFloorBeamsAssembly type, containing long. floor + beam assemblies + + + + + + + + + + + + + + + + + + + longFloorBeamType + + + longFloorBeam type, containing a long. floor beam + definition + + + + + + + + + + + + + + + + + + + + Luggage compartment elements + + + Luggage compartment element collection type + + + + + + + + + + Luggage compartment element for use in the decks + + + + + + + + + + + + + Luggage compartments + + + + + + + + + + Luggage compartment + + + + + + + + + + + + + + Additional Center Tanks + + + + + + + + + + + + + + Additional center tank + + + + + + + + + + + + + Main actuator + + + + Definition of the landing gear main actuator. + + + + + + + + + + + Reference to the main actuator uID of the + landing gear + + + + + + + + + + + + + + Main landing gear + + + List of main gears + + + + + + + + + + + + + + + + + + + mainStrutInterfaceDefinitionsType + + + HighWingCenterFuselage main strut interface definitions + + + + + + + + + + + + + + + + + + + + + + mainStrutFuselageAttachmentType + + + HighWingCenterFuselage / main strut attachment to + fuselage frame and stringer + + + + + + + + + + + + + reference to the structural element that comprises this connection. + + + + + + + + + + + + + + maintenanceCostType + + + + + + + + + + + + + + + + + + + + + + + + mAirConditioningType + + + + + + + + + + + + + Air conditioning mass description + + + + + + + + + + + + + + Mass breakdown + + + + + 1. General + + + The + massBreakeDown + is subdivided in + designMasses + , + fuel + , + payload + and + mOME + (operating empty mass). + + + designMass + + The design masses contain the overall values for + mTOM and so forth. These should be listed as specified by the + TLAR or found from initial sizing. + + fuel + and + payload + + The fuel and payload nodes should contain maximum + values, i.e. full fuel tanks, all passengers on board and full + cargo holding. These values may exceed the maximum allowable + take-off mass as the actual loading of the aircraft should be + specified in the weight and balance section of the aircraft. + + + mOEM + + + The operation empty mass structure is based on the Airbus Mass + Standard brake down [AIRBUS MASS STANDARD 2008]. The + operator’s mass empty (OME) is defined by the sum of the + following component masses: + + operator’s items + manufacturer’s mass empty (MME) + + + + + + + 2. massDescription + + + Each sub component has the following + massDescription + which include a: + + Name + Description + parentUID + Mass value + Mass location + Mass orientation + Mass Inertia. + + + + The + massdescription + can be found at the + designMasses + direct under each item. At the + fuel + , + payload + and + mOME + under massDescription in each item and sub item. + + Concerning symmetry please note that any item + referenced by its UID, e.g. wingUID, accounts for the complete + component, e.g. right and left side. Hence for these items + their complete mass needs to be specified. If the mass of + geometricallly symmetrical components is different, please use + the symmetry modifyers for UIDs: _symm and _mirror. See also + the overall CPACS definition section on symmetry + + + + + + + + + + + + + + + + + + + + + + + + + Mass composition + + + + + + + + + + + + + + + + + + + Mass flow + + + + + + + + + + + Mass flow value + + + + + + + + + + + + + + + + + + Mass flow + + + + + + + + + + + Mass flow value + + + + + + + + + + + + + + + + + + Mass inertia + + + massInertiaType + + + + + + + + + + + + + + + + + + + + + + + + massInertiaVectorType + + + + + + + + + + + + + + + + + + + + + + + + + + + materialDefinitionForProfileBasedPointType + + + MaterialDefinitionForProfileBased type, containing a + material definition (Reference to material and thickness) for + profile based objects, addition point reinforcements + + + + + + + + + + uID of the profile point to which the + additional stiffness shall be applied. + + + + + uID of a material definition. + + + + + + cross sectional area of additional long. + stiffener at strctural element point + + + + + optional auxiliary parameter for special use + (no physical meaning) + + + + + optional auxiliary parameter for special use + (no physical meaning) + + + + + + + + + + + + + Definition of the properties of the structural + profile sheet + + + MaterialDefinitionForProfileBased type, containing a + material definition (Reference to material and thickness) for + profile based objects. + + + + + + + + + + + UID of the sheet to which the material + properties shall be applied + + + + + + Predefined ID of the sheet of a standard profile + + + + + + + + + + + + + + + + + + Length of the sheet of a standard profile [m] + + + + + + + + + uID of a composite definition. + + + + + + Orthoropy direction of the composite. + + + + + + Scaling factor of the composite thickness. + + + + + + + + uID of a material definition. + + + + + + Absolute thickness of the material [m] + + + + + + + + + + + + + + + + Material Definition + + + MaterialDefinition type, containing a material + definition (Reference to material and thickness) + + + + + + + + + choice between composite / isotropic material + definition + + + + + uID of a composite definition. + + + + + + Orthotropy direction of the composite. + + + + + + Scaling factor of the composite thickness. + Absolute thicknesses are defined in each composite material + separately + + + + + + + uID of a material definition. + + + + + + Absolute thickness of the material. + + + + + + + + + + + + + + + Materials + + + Materials type, containing material and composite data. + A material describes the properties of a certain material. + Several materials can be combined within one composite. + + + + + + + + + + + + + + + + + + + + + Material + + + + Definition of the material properties for one of the following + material types: + + isotropic materials + anisotropic 2D and 3D materials + orthotropic 2D and 3D materials + + The nonemclature is adopted from [1] to define the material properties in an orthotogonal 1-2-3 + coordinate system. This may be illustrated by the stresses of a three-dimensional cube: + + + + + [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. + + + + + + + + + + + + Name of the material + + + + + Description of the material + + + + + Material density [kg/m3] + + + + + + + + + + + + Reference temperature for thermal expansion + coefficient [K] + + + + + + + + + + + + + + + + + mAutomaticFlightSystemType + + + + + + + + + + + + + Automatic flight system mass description + + + + + + + + + + + + + + mAuxillaryPowerUnitType + + + + + + + + + + + + + Auxiliary power unit masse description + + + + + + + + + + + + + + Axle + + + + + + + + + + + + + + Axle mass description + + + + + + + + + + + + + + + + mBellyFairingsType + + + + + + + + + + + + + + + + + + + + + + + mBleedAirSystemType + + + + + + + + + + + + + Bleed air system mass description + + + + + + + + + + + + + + Bogie + + + + + + + + + + + + + + Bogie mass description + + + + + + + + + + + + + + + + mBulkCargosType + + + + + + + + + + + + + + + + + + + + + + + mBulkCargoType + + + + + + + + + + + + + + + + + + + + + + mBulkheadsType + + + + + + + + + + + + + + + + + + + + + + + mCabinFloorsType + + + + + + + + + + + + + + + + + + + + + + + mCabinLightingsType + + + + + + + + + + + + + + + + + + + + + + + mCargoFloorsType + + + + + + + + + + + + + + + + + + + + + + + mCargoLiningsType + + + + + + + + + + + + + + + + + + + + + + + mCargoLoadingsType + + + + + + + + + + + + + + + + + + + + + + + Cargo masses + + + + + + + + + + + + + Cargo masses description + + + + + Cargo mass description + + + + + + + + + + + + + + + mCarriagesType + + + + + + + + + + + + + + + + + + + + + + + mCarryOnsType + + + + + + + + + + + + + + + + + + + + + + + mCarryOnType + + + + + + + + + + + + + + + + + + + + + + mCateringsType + + + + + + + + + + + + + + + + + + + + + + + mCellsType + + + + + + + + + + + + + + + + + + + + + + + mCockpitLightingsType + + + + + + + + + + + + + + + + + + + + + + + mCommunicationType + + + + + + + + + + + + + Communication mass description + + + + + + + + + + + + + + mComponentSegmentsType + + + + + + + + + + + + + + + + + + + + + + + mComponentSegmentType + + + + + + + + + + + + + + + + + + + + + + + + + + + + + mControlSurfaceSupportsType + + + + + + + + + + + + + + + + + + + + + + + mControlSurfaceSupportType + + + + + + + + + + + + + + + + + + + + + + + + + mCrewMembersType + + + + + + + + + + + + + + + + + + + + + + + mCrewSeatsType + + + + + + + + + + + + + + + + + + + + + + + mDeIcingType + + + + + + + + + + + + + De-icing mass description + + + + + + + + + + + + + mDocumentsToolsType + + + + + + + + + + + + + + + + + + + + + + + mDoorsType + + + + + + + + + + + + + + + + + + + + + + + Mechanical power + + + + + + + + + + + Mechanical power value [W] + + + + + + + + Torque [Nm] + + + + + + + Force [N] + + + + + + + + + + + + + + + Mechanical power + + + + + + + + + + + Mechanical power value [W] + + + + + + + + Torque [Nm] + + + + + + + Force [N] + + + + + + + + + + + + + + + mElectricalDistributionType + + + + + + + + + + + + + Electrical distribution mass description + + + + + + + + + + + + + + mElectricalGenerationType + + + + + + + + + + + + + Electrical generation mass description + + + + + + + + + + + + + + mEmergencyEquipmentsType + + + + + + + + + + + + + + + + + + + + + + + mEmergencyOxygenSystemsType + + + + + + + + + + + + + + + + + + + + + + + mEmptyULDsType + + + + + + + + + + + + + + + + + + + + + + + mEmptyULDType + + + + + + + + + + + + + + + + + + + + + + Engine APU oils + + + + + + + + + + + + + + Engine APU oil + + + + + + + + + + + + + mEngineControlType + + + + + + + + + + + + + Engine control mass description + + + + + + + + + + + + + + mEquippedEnginesType + + + + + + + + + + + + + + Equipped engines mass description + + + + + + + + + + + + + + + mExtLightingsType + + + + + + + + + + + + + + + + + + + + + + + mFireProtectionType + + + + + + + + + + + + + Fire protection mass description + + + + + + + + + + + + + + mFixedGalleysType + + + + + + + + + + + + + + + + + + + + + + + mFixedLeadingEdgesType + + + + + + + + + + + + + + + + + + + + + + + mFixedLeadingEdgeType + + + + + + + + + + + + + + + + + + + + + + mFixedTrailingEdgesType + + + + + + + + + + + + + + + + + + + + + + + mFixedTrailingEdgeType + + + + + + + + + + + + + + + + + + + + + + + + mFlightControlsType + + + + + + + + + + + + + Flight controls mass description + + + + + + + + + + + + + + mFloorCoveringsType + + + + + + + + + + + + + + + + + + + + + + + mFramesType + + + + + + + + + + + + + + + + + + + + + + + mFreshWaterSystemsType + + + + + + + + + + + + + + + + + + + + + + + mFuelSystemType + + + + + + + + + + + + + Fuel system mass description + + + + + + + + + + + + + + Fuel mass + + + + + + + + + + + + + Fuel mass description + + + + + + + + + + + + + + Mass + + + + + + + + + + + + + Furnishing mass description + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + mFuselagesStructureType + + + + + + + + + + + + + Fuselages structure mass description + + + + + + + + + + + + + + + mFuselageStructureType + + + + + + + + + + + + + Fuselage structure mass description + + + + + + + + + + + + + + + + + + + + + + + + + + mHydraulicDistributionType + + + + + + + + + + + + + Hydraulic distribution mass description + + + + + + + + + + + + + + mHydraulicGenerationType + + + + + + + + + + + + + Hydraulic generation mass description + + + + + + + + + + + + + + In-flight entertainment systems + + + + + + + + + + + + + + + + + + + + + + + mInstrumentPanelType + + + + + + + + + + + + + Instrument panel mass description + + + + + + + + + + + + + + mInsulationsType + + + + + + + + + + + + + + + + + + + + + + + mIntegratedModularAvionicsType + + + + + + + + + + + + + Integrated modular avionics mass description + + + + + + + + + + + + + + mInterGasSystemType + + + + + + + + + + + + + Inter gas system mass description + + + + + + + + + + + + + + Mission definitions + + + + + General description + Specifies mission profiles required for the performance evaluation of air vehicles (aircraft, rotorcraft, etc.). The missionDefininitions node is constructed in such a way, that all civil aircraft missions and missions from MIL-STD-3013A can be specified. + > + + + Hierarchical buildup of the mission definition + + The mission definition is built-up in a hierarchical way. As the topmost element of the hierarchical mission definition, missions are created within the missions node. Here, one or more segmentBlocks are referenced. These again link to a sequence of segments, making up parts of the missions: + + + + + + + <missions> + + + containing the + <startCondition> + and a sequence of + <segmentBlockUIDs> + + + + + <segmentBlocks> + + + + grouping multiple + <segments> + and providing overall information concerning the block of segments: + + + + + constraints in the form of an + endCondition + or given + flightPath + , + + + variableSegments + and the corresponding + variableConditions + in case a segment should be adjusted such to meet the + segmentBlock + 's + endCondition + , + + + fuelPlanningType + ( + designFuel + , + reserveFuel + , + additionalFuel + ), + + + segmentDirection + and + numberOfRepetitions + . + + + + + + + + <segments> + + + + containing detailed information per segment: + + + EITHER + + + + + segmentType + , + + + endConditions + , + + + constraints + , + + + environmentalConditions + + + + + OR + massFraction + + + OR + mass + + + + + + + + startConditions, constraints, endConditions and the relationalOperator attribute + + the startCondition is provided at the mission node. Each subsequent segmentBlock/segment ends by the provided endCondition. + + + + <startCondition> + + start condition of the mission (can be an airfield or mid-air condition) + + + + <endCondition> + + + specific end condition for a + segmentBlock + or + segment + (e.g.: an altitude or velocity) + + + + + <constraint> + + + specific performance settings for a + segmentBlock + or + segment + (e.g.: a cruise Mach number) + + + + + attribute  + @relationalOperator + + + Indicate how conditions should be interpreted: + + + + enum: „lt“, „le“, „eq“, „ne“, „ge“, „gt“ + , + + + Examples: + + + 0.78 +1800 + ]]> + + + + + + + + + + + + + Example implementation for a civil transport mission + + + + + + In the figure above, an example for a civil aircraft transport mission is provided. + + + The mission starts at a position of 0, 0, 0 with 0 velocity, as provided by the + startCondition + of the + mission + node. Furthermore, the environmental conditions are provided: ISA atmosphere with a + deltaTemperature + of 0 [K]. The mission consists of three + segmentBlocks + : a designMission, reserves and the taxiIn + segmentBlock + . + + + + example mission + this is an example mission + + 0.0 + + 0.0 + 0.0 + 0.0 + + + ISA + 0.0 + + + + designMission + reserves + endPhase + + + ]]> + + + The designMission + segmentBlock + is shown below. It provides a set of five segments, together making up a mission with a range of 1000 [nm] or 1852 [km]. The “cruise” segment is the variable segment, which thereby should have a range of: + 1852000 – range(climb) – range(descent) + , provided the taxiOut and takeOff segments are not providing any range credit. The fuel burned during this + segmentBlock + should be added to the + designFuel + , the + segmentDirection + is provided for illustration purposes. + + + + + design mission + segment block for the design mission + + + 1852000 + + + + + cruise + range + + + designFuel + outbound + + taxiOut + takeOff + climb + cruise + descent + + + + + ]]> + + + The first and second segment are providing input for the part of the + segmentBlock + that doesn’t need simulation. During the taxiOut phase, 50 [kg] of fuel is burned. The takeOff phase has a duration of 30 [sec]. + + + + taxi out + taxi out segment + massFraction + 50 + + + take off + take off segment + takeOff + + 00:00:30 + + + ]]> + + + The rest of the segments make-up the flying part of the + designMission + . The climb phase, ending at an altitude of FL330 or 10058.4 [m], provides a constraint-lapse having discrete steps, typical for transport aircraft (a 250 kt / 300 kt / M 0.78 climb profile). Through the + referenceEndconditionUID + “altClimb”, a link to the altitude + endCondition + of the segment at the basis of this climb profile is provided. + + + + + + Altitude from + + + Altitude to + + + calibratedAirspeed + + + machNumber + + + + 0.0 [m] + 0.303 * 10058.4 = 3047.7 [m] + ≤ 128.61 [m/s] + ≤ 0.78 [-] + + + 0.303 * 10058.4 = 3047.7 [m] + 10058.4 [m] + ≤ 154.33 [m/s] + ≤ 0.78 [-] + + + + + The cruise phase is not fixed to a certain altitude and has no + endCondition + , since its range is determined by the + segmentBlock + information. The descent phase makes sure the vehicle lands at an altitude of 0 [m]. In this case, since the values are not explicitly provided, it is up to the mission simulation software to determine, when the cruise phase ends and the descent phase starts. + + + + climb + climb with: speed @ MFCS (set to machNumber le 0.78 [-]), altitude @ FL330 + climb + + + 10058.4 + + + + + altitude + 0.0;0.303 + discrete + 128.61;154.33 + 0.78;0.78 + velocity + + + + + cruise + cruise with: speed @ optimum cruise speed, altitude @ optimum cruise altitude + cruise + + + + descent to MSL + descent to MSL altitude + descent + + + 0 + + + + ]]> + + + Two more + segmentBlocks + make up the mission. The “reserves” + segmentBlock + provides information for the cruise to alternate airport and loitering phase and the corresponding burnt fuel is considered + reserveFuel + . The mission ends with a landing and taxiIn phase within the “endPhase” + segmentBlock + , of which the burnt fuel is considered + additionalFuel + . The following then holds: + blockFuel + = + designFuel + + + additionalFuel + . + + + + + + + + + + + + + + + + + + + + + + + + + + + UID of the runway + + + + + + + Offset from runway threshold in cartesian coordinates in the runway coordinate system + + + + + + + + + + + + + + Setting default and specific performance maps to be used for a model + + + + + + + + + + Default performance map which is used if no other performance map + is assigned through the specificPerformanceMap node + + + + + List of specific performance maps used on dedicated mission segments or pointPerformance requirements + + + + + + + + + + + + + Specific performance settings for the segmentBlock (e.g.: a cruise Mach number) + + + + + + + + + + + + + + + + + + + + Segment blocks + + + A list of segment blocks. A segment block specifies conditions for a predefined combination of segments (e.g.: setting the total range for a block of segments consisting of a takeOff, climb, cruise, descent and landing segment). + + + + + + + + + + + + + + + + + + + Segment block + + + A segment block specifies conditions for a predefined combination of segments (e.g.: setting the total range for a block of segments consisting of a takeOff, climb, cruise, descent and landing segment). + + + + + + + + + + Name + + + + + Description + + + + + + Segment direction. Either 'outbound' or 'inbound'. Only needed for radiusOfAction kind of missions. + + + + + + + + + + + + + + List of segment uID's making up the segmentBlock. These should be ordered, such that the segment connections are correct. + + + + + + + Specifies to which type of mass the segment fuel mass + should be added (blockFuel = designFuel + additionalFuel; Total fuel requirement + = blockFuel + reserveFuel; designFuel = the fuel of the segmentBlock is part of the design mission) + + + + + + + + + + + + + + + + Number of repetitions of this segment block, e.g. to perform repeated holding patterns + + + + + + + + + + + + + + + + End condition + + + + + Specifies the end conditions for a segment or segment block (e.g.: an altitude or velocity). If a phase has no endCondition, it will base its endCondition on the segmentBlock settings (e.g.: it is the cruise segment, retrieving its total length based on the length of the segmentBlock minus all other segment lengths available within the segmentBlock). + + + + + + + + + + + + + + Calibrated airspeed at the end of the segment [m/s] + + + + + + + + + + + + + + Mach number at the end of the segment + + + + + + + + + + + + + + + Position at the end of the segment in xyz coordinates + + + + + + + Position at the end of the segment in geo coordinates + + + + + + + + Reference to the runway on which the segment ends + + + + + + + + + + + + + + + + massFraction ending the segment [-] + + + + + + + + + + + + + + massFraction of remaining fuel ending the segment [-] + + + + + + + + + + + + + + Absolute mass of remaining fuel ending the segment [kg] + + + + + + + + + + + + + + Consumed fuel ending the segment [kg] + + + + + + + + + + + + + + Power fraction of remaining at the end of the segment + + + + + + + + + + + + + + Absolute power left ending the segment [W] + + + + + + + + + + + + + + Consumed power ending the segment [W] + + + + + + + + + + + + + + + + Flight heading at the end of the segment in compassAngle with reference to true North [deg] + + + + + + + + + + + + + + Total change of heading angle during segment (a full turn is 360 degrees) [deg] + + + + + + + + + + + + + + + Flown distance ending the segment + + + + + + + + + + + + + + + Duration of the segment [hh:mm:ss] + + + + + + + + + + + + + + UTC time at end of segment [hh:mm:ss] + + + + + + + + + + + + + + + Specific excess power at the end of the segment + + + + + + + + + + + + + + Rate of climb ending the segment [m/s] + + + + + + + + + + + + + + Achieved flightPathAngle ending the segment [deg] + + + + + + + + + + + + List of stores released in the segment. The corresponding weightAndBalance vector for retrieving the new state as well as a potential change in aerodynamicPerformanceMap (if external stores are released) should be reflected within the configuration node at model level. + + + + + + + + + + + + + + Mission segments + + + A collection of mission segments which can be reused to define missions. + + + + + + + + + + + + + + + + + + + Segment + + + Definition of a mission segment which can be used to define missions. + + + + + + + + + + Name + + + + + Description + + + + + Type of the mission segment (takeOff, clime, cruse, ...) + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Indication whether the distance flown during the segment is to be taken into account in the segmentBlock's distance calculation. + + + + + + Environmental conditions. If the environmentalCondition is not provided at segment level, the conditions of the + previous segment are inherited (this inheritance can continue until the startCondition, where the initial + environmentalConditions are provided). + + + + + + + Fuel mass + + + + + + + + + + + + + + + + + + + + Start conditions + + + Conditions which define the start of a mission + + + + + + + + + + + Calibrated airspeed at the start of the mission [m/s] + + + + + Mach number at the start of the mission + + + + + + + Global coordinate at the start of the mission in xyz coordinates + + + + + Global coordinate at the start of the mission in geographic coordinates (longitude, latitude, altitude) + + + + + + UID of the runway at which the + mission starts + + + + + + + + Flight heading at the start of the mission, in compassAngle with reference to true North + + + + + + UTC time at start of mission + + + + + + + + + + + + + + + + UID of the runway + + + + + + + Offset from runway threshold in the runway coordinate system + + + + + + + + + + + + + + Missions + + + A list of missions. + + + + + + + + + + + + + + + + + + + Mission + + + Contains a list of segmentBlock uID's forming the mission along with additional mission information. + + + + + + + + + + Name + + + + + Description + + + + + + + List of segmentBlock uID's forming the mission. Segments must first be grouped in segmentBlocks to be assigned to a mission. + + + + + + + + + + + + + + + mLandingGearsType + + + + + + + + + + + + + + Landing Gears mass description + + + + + + + + + + + + + + + mLandingGearSupportsType + + + + + + + + + + + + + + + + + + + + + + + mLandingGearType + + + + + + + + + + + + + + Landing Gear mass description + + + + + + + + + + + + + + + + + + + + + + mLavatoriesType + + + + + + + + + + + + + + + + + + + + + + + mLiningsType + + + + + + + + + + + + + + + + + + + + + + + Mass + + + + + + + + + + + + + Manufacturer empty mass description + + + + + + + + + + + + + + + + + + mMillitarySystemsType + + + + + + + + + + + + + Military systems mass description + + + + + + + + + + + + + + mMoveableLeadingEdgesType + + + + + + + + + + + + + + + + + + + + + + + mMoveableLeadingEdgeType + + + + + + + + + + + + + + + + + + + + + + + + mMoveablesType + + + + + + + + + + + + + + + + + + + + + + + + mMoveableTrailingEdgeType + + + + + + + + + + + + + + + + + + + + + + + + mNavigationType + + + + + + + + + + + + + Navigation mass description + + + + + + + + + + + + + + Monetary values + + + + + + + + + + + + + + + + + + + + + + + Mass + + + + + + + + + + + + + Operator items mass description + + + + + + + + + + + + + + + + + + + + + + + + + + + + mOverheadBinsType + + + + + + + + + + + + + + + + + + + + + + + mPartStowDoorsType + + + + + + + + + + + + + + + + + + + + + + + mPassengersType + + + + + + + + + + + + + + + + + + + + + + + mPassengerType + + + + + + + + + + + + + + + + + + + + + + Passengers masses + + + + + + + + + + + + + Passanger masses Description + + + + + + Passanger mass Description + + + + + + + + + + + + + + Payload mass + + + + + + + + + + + + + Payload mass description + + + + + + + + + + + + + + + Pintle struts + + + + + + + + + + + + + + Pintle struts mass description + + + + + + + + + + + + + + + Mass + + + + + + + + + + + + + Power units mass description + + + + + + + + + + + + + + + + + + + + mPylonAttachmentsType + + + + + + + + + + + + + + + + + + + + + + + mPylonsType + + + + + + + + + + + + + + Pylons mass description + + + + + + + + + + + + + + + Removable crew rests + + + + + + + + + + + + + + Removable crew rest + + + + + + + + + + + + + mRibsType + + + + + + + + + + + + + + + + + + + + + + + mRibType + + + + + + + + + + + + + + + + + + + + + + mSeatsType + + + + + + + + + + + + + + + + + + + + + + + mShellsType + + + + + + + + + + + + + + + + + + + + + + + + mShellType + + + + + + + + + + + + + + + + + + + + + + + + + Side Struts + + + + + + + + + + + + + + Side struts mass description + + + + + + + + + + + + + + + mSkinPanelsType + + + + + + + + + + + + + + + + + + + + + + + mSkinsType + + + + + + + + + + + + + + + + + + + + + + + mSparCellsType + + + + + + + + + + + + + + + + + + + + + + + mSparSkinsType + + + + + + + + + + + + + + + + + + + + + + + mSparsType + + + + + + + + + + + + + + + + + + + + + + + mSparType + + + + + + + + + + + + + + + + + + + + + + + + mSpecialStructuresType + + + + + + + + + + + + + + + + + + + + + + + mSpoilersType + + + + + + + + + + + + + + + + + + + + + + + mStringersType + + + + + + + + + + + + + + + + + + + + + + + Mass + + + + + + + + + + + + + Structure mass description + + + + + + + + + + + + + + + + + Mass + + + + + + + + + + + + + Systems mass description + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Toilet fluids + + + + + + + + + + + + + + Toilet fluid + + + + + + + + + + + + + mTrailingEdgeDevicesType + + + + + + + + + + + + + + + + + + + + + + + mTrailingEdgeDeviceType + + + + + + + + + + + + + + + + + + + + + + + + mULDContentsType + + + + + + + + + + + + + + + + + + + + + + + mULDContentType + + + + + + + + + + + + + + + + + + + + + + UnusableFuels + + + + + + + + + + + + + + Unusable fuel + + + + + + + + + + + + + mVacuumWasteSystemsType + + + + + + + + + + + + + + + + + + + + + + + mWallsType + + + + + + + + + + + + + + + + + + + + + + + mWasteWaterSystemsType + + + + + + + + + + + + + + + + + + + + + + + Water reservoirs + + + + + + + + + + + + + + Water reservoir + + + + + + + + + + + + + Wheels + + + + + + + + + + + + + + Wheels mass description + + + + + + + + + + + + + + + mWindowsType + + + + + + + + + + + + + + + + + + + + + + + mWingBoxType + + + + + + + + + + + + + + + + + + + + + + + + + mWingsStructureType + + + + + + + + + + + + + Wings structure mass description + + + + + + + + + + + + + + + mWingStructureType + + + + + + + + + + + + + Wing structure mass description + + + + + + + + + + + + + + + Center cowl + + + + + The + centerCowl + is defined by the rotation of a given curve profile (referenced via + curveUID + ) around the + x + -axis. + + + + + + + + + + + + + + + Offset of the rotation curve in x-direction + + + + + UID of the curve profile (vehicles/profiles/curveProfiles/..) + + + + + + + + + + + + + + Nacelle cowl + + + + Describes the cowl geometry for nacelles + using sections positioned around the + rotational center of the engine. + + + + + + + + + + + + + + + + + + + + + + + Guide curves + + + + + + + + + + + + + + + + + + + Guide curve + + + + + The following figure shows the basic setup of the guide curves. + They always start at a given ζ-position ( + fromZeta + ) on the profile of the specified start section ( + startSectionUID + ) and end at the ζ-position ( + toZeta + ) on the profile of the subsequent section. + The relative coordinates of the guide curves are specified in + cpacs/vehicles/profiles/guideCurves + and referenced via its + uID + . + + + + + + Note + : Guide curves and profiles must result in a valid curve network. + + + The guide curve points are interpreted as ( + Δr + and + Δx + ) offsets from a cubic polynomial. + This polynomial serves as a baseline for guide curves between segments located on different radial positions with smooth transitions: + + + + + + Note + : Currently, the nacelles do not have an explicit guide curve type but employ the standard guide curve definition, which is used in wings and profiles. + Therefore, the parameters have a different meaning: + + + + Standard guide curve parameter + Nacelle guide curve equivalent + Description + + + rX + + φ + + + Independent variable normalized to + [0,1] + + + + rY + + Δx + + + Orthogonal offset (translation in + x + -direction) + + + + rZ + + Δr + + Radial offset + + + + + + + + + + + + + + Name + + + + + + + Description + + + + + + + UID of the guide curve profile + + + + + + + UID of the start section + + + + + + + Curve coordinate of the referenced section profile at which the guide curve shall start. + Valid values are in the interval -1,..,1. + + + + + + + Curve coordinate of the profile following the referenced section profile. + It defines where the guide curve ends. + Valid values are in the interval -1,..,1. + + + + + + + + + + + + + + nacelleProfilesType + + + Nacelle profiles type, containing nacelle profile geometries. + See profileGeometryType for further documentation + + + + + + + + + + + + + + + + + + + Sections + + + + + + + + + + + + + + + + + + + + + + Section + + + + + An engine nacelle is defined by sections, where at least one and up to an infinite number of sections can be specified. + Lofting of the nacelle surface along the sections is done in cylindrical coordinates. + The + coordinate origin refers to the center of the fan + , i.e. the sections and their profiles are typically shifted in negative x-direction. + + + Note + : In the current CPACS release, transformations are still labeled as Cartesian coordinates. + It is current work in progress to explicitly introduce cylindrical coordinates. + Until this is implemented in a future CPACS release, the implicit conventions listed below apply: + + + + Translation component + Cylindrical coordinate equivalent + Description + + + + x + + + ϑ + + + Rotation angle around + x + + + + + y + + + h + + Horizontal translation + + + + z + + + r + + Radial translation + + + + The following example illustrates the setup of a nacelle with 4 sections. + These are rotated by 0, 120, 180 and 240 degrees around the + x + -axis (given by + translation/x + ). + To illustrate the possible transformations, the profile of the upper section is shifted slightly further in the negative + x + -direction ( + translation/y + ), while the lower section has a smaller radial distance from the rotation axis ( + translation/z + ). + In addition, the sections are scaled differently ( + transformation/scaling + ; not shown in the example figures) in order to create a straight trailing edge and to realize a flattened profile near the ground. + + + The following example also shows the profile cut-outs due to the radially symmetric inner region of the nacelle defined by the + rotationCurve + . For detailed information, please refer to the documentation of the + rotationCurve + element. + + + + + + The first section is not rotated ( + x=ϑ=0 + ), but shifted vertically in negative direction ( + y=h=-0.257 + ). + The radial distance is given by + z=r=0.365 + : + + + + Upper section + + + 1.055 + 1 + 1 + + + 0.0 + -0.257 + 0.365 + + + fanCowlUpperSectionProfile + + ]]> + + + The second section is rotated around the + x + -axis ( + x=ϑ=120 + ) as well as scaled by a factor of 1.1 in its profile height: + + + + Inboard section + + + 1 + 1 + 1.1 + + + 120.0 + -0.2 + 0.365 + + + fanCowlUpperSectionProfile + + ]]> + + + The third section is rotated around the + x + -axis by 180° and scaled by a factor of 0.8 in its profile height: + + + + Lower section + + + 1 + 1 + 0.8 + + + 180.0 + -0.2 + 0.33 + + + fanCowlUpperSectionProfile + + ]]> + + + + + + + + + + + + Name + + + + + Description + + + + + + UID of the profile + + + + + + + + + + + + + + Noise + + + + + + + + + + + + + FAR approach noise level + + + + + FAR sideline noise level + + + + + FAR take-off noise level + + + + + + + + + + + + + Nose landing gears + + + List of nose gears + + + + + + + + + + + + + + + + + + + Operating empty mass + + + + + + + + + + + + + Operating empty mass description + + + + + + + + + + + + + + + + operationalCasesType + + + + + + + + + + + + + + + + + + + + + + operationalCaseType + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Operation Limit Increments + + + Changes of the deltas of operation limit angles with respect to the corresponding increment aeroPerformanceMaps. + Values are specified as an array with same indices like the corresponding increment map. + + + + + + + + + + Minimum delta angle of attack [deg] + + + + + Maximum delta angle of attack [deg] + + + + + + + + + + + + + + Orthotropic material properties for 2D materials + + + + + Defines the material properties for an orthotropic material in the plane stress state (i.e., shell). The strain-stress relationship is defined as: + + + + Inverting the strain-stress relation and introducing thermal expansion yields: + + + + with: + + + + The terminology refers to the following literature: + + [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. + + + + + + + + + + + + Young's modulus in material direction 1 [N/m^2] + + + + + Young's modulus in material direction 2 [N/m^2] + + + + + Shear modulus in material in 2-3 plane [N/m^2] + + + + + Shear modulus in material in 3-1 plane [N/m^2] + + + + + Shear modulus in material in 1-2 plane [N/m^2] + + + + + Poisson's ratio + + + + + Thermal expansion coefficient in material direction + 1 [1/K] + + + + + Thermal expansion coefficient in material direction + 2 [1/K] + + + + + Thermal conductivity of the material in material direction 1 [W/(m*K)] + + + + + + Thermal conductivity of the material in material direction 2 [W/(m*K)] + + + + + + Allowable stress for tension in material direction 1 + [N/m^2] + + + + + Allowable stress for compression in material + direction 1 [N/m^2] + + + + + Allowable stress for tension in material direction 2 + [N/m^2] + + + + + Allowable stress for compression in material + direction 2 [N/m^2] + + + + + Allowable stress for shear [N/m^2] + + + + + + Allowable strain for tension in material direction 1 + + + + + + Allowable strain for compression in material + direction 1 + + + + + Allowable strain for tension in material direction 2 + + + + + + Allowable strain for compression in material + direction 2 + + + + + Allowable strain for shear + + + + + + + + + + + + + + Orthotropic material properties for 3D materials + + + + + Defines the material properties for an elastic orthotropic material in three spatial directions (i.e., solid). The strain-stress relationship is defined as: + + + + Note that nuij is related to nuji by: + + + + The terminology refers to the following literature: + + [1] R. M. Jones, Mechanics Of Composite Materials, 2 New edition. Philadelphia, PA: Taylor and Francis Inc, 1998. + + + + + + + + + + + + Young's modulus in material direction 1 [N/m^2] + + + + + Young's modulus in material direction 2 [N/m^2] + + + + + Young's modulus in material direction 3 [N/m^2] + + + + + Shear modulus in the 2-3 plane [N/m^2] + + + + + Shear modulus in the 3-1 plane [N/m^2] + + + + + + Shear modulus in the 1-2 plane [N/m^2] + + + + + Poisson's ratio in in 2-3 plane + + + + + Poisson's ratio in in 3-1 plane + + + + + Poisson's ratio in in 1-2 plane + + + + + Thermal expansion coefficient in material direction + 1 [1/K] + + + + + Thermal expansion coefficient in material direction + 2 [1/K] + + + + + Thermal expansion coefficient in material direction + 3 [1/K] + + + + + Thermal conductivity of the material which couples heat flux in material direction 2 with temperature gradient in material direction 3 [W/(m*K)] + + + + + Thermal conductivity of the material which couples heat flux in material direction 3 with temperature gradient in material direction 1 [W/(m*K)] + + + + + + Thermal conductivity of the material which couples heat flux in material direction 1 with temperature gradient in material direction 2 [W/(m*K)] + + + + + + Allowable stress for tension in material direction 1 + [N/m^2] + + + + + Allowable stress for compression in material + direction 1 [N/m^2] + + + + + Allowable stress for tension in material direction 2 + [N/m^2] + + + + + Allowable stress for compression in material + direction 2 [N/m^2] + + + + + Allowable stress for tension in material direction 3 + [N/m^2] + + + + + Allowable stress for compression in material + direction 3 [N/m^2] + + + + + Allowable stress for shear in 2-3 plane [N/m^2] + + + + + + Allowable stress for shear in 3-1 plane [N/m^2] + + + + + Allowable stress for shear in 1-2 plane [N/m^2] + + + + + + Allowable strain for tension in material direction 1 + + + + + + Allowable strain for compression in material + direction 1 + + + + + Allowable strain for tension in material direction 2 + + + + + + Allowable strain for compression in material + direction 2 + + + + + Allowable strain for tension in material direction 3 + + + + + + Allowable strain for compression in material + direction 3 + + + + + Allowable strain for shear in 1-3 plane + + + + + + Allowable strain for shear in 1-3 plane + + + + + + Allowable strain for shear in 1-2 plane + + + + + + + + + + + + + + outerCutOutProfileType + + + + + + + + + + + + + + + + + + + + + + + Container for parameter definitions + + + Contains a of the design parameter definitions. + + + + + + + + + + + + + + + + + + + + Parameter definition for design studies. + + + Contains a name for the design parameter to give semantic meaning to parameters used in design studies. + + + + + + + + + + + Name of parameter + + + + + + + + + + + + + + paxCrossBeamsAssemblyType + + + PaxCrossBeamsAssembly type, containing pax crossBeam + assemblies + + + + + + + + + + + + + + + + + + + paxCrossBeamStrutsAssemblyType + + + PaxCrossBeamStrutsAssembly type, containing pax + crossBeam strut assemblies + + + + + + + + + + + + + + + + + + + paxDoorsAssemblyType + + + PaxDoorsAssembly type, containing pax door assemblies + + + + + + + + + + + + + + + + + + + + payloadGlobalType + + + + + + + + + + + + + + + + + + + + + + + Selection of performance maps + + + + + + + + + + Engine performance map selection + + + + + Aerodynamic performance map selection + + + + + + + + + + + + + Configurations which apply for this performance requirement + + + + + + + + + + + + + + + + Default configuration uID + + + + + + + + + + + + + + + Performance requirements + + + + + + + + + + + + + + + + + + + + + + + + + + performanceTargetsGlobalType + + + + + + + + + + + + + + + + + + + + + + + + + + + + Multi-phase mass flow + + + + + + + + + + + Pressure + + + + + + + Temperature + + + + + + + + + + + + + + + Multi-phase mass flow + + + + + + + + + + + Pressure + + + + + + + Temperature + + + + + + + + + + + + Pintle strut(s) (Assumption: one end of the strut will connect to the main strut and the other end will be given as endPoint) + + + + + Pintle strut (one or two pintle struts are supported) + + + + + + + + + + + Piston + + + + + Geometric description and material properties of the + landing gear piston. The figure below shows the condition of the + uncompressed piston, where the length of the exposed part is the + sum of the + maxSpringDeflection + and the + compressedExternalLength + : + + + + + + + + + + + + + + + Length of the piston + + + + + + Maximum spring deflection of the piston (difference between minimum and maximum deflection) + + + + + Length of the piston that remains outside of the main strut in fully compressed state + + + + + + + + + + + + + + Points on plasticity curve of material + (min. 1 point) + + + + + + + + + + + + plasticityCurvePointType + + + + + + + + + + + + + Tangent modulus [N/m^2] + + + + + True stress [N/m^2] + + + + + + + + + + + + + plasticityCurvesType + + + + + + + Plastification curve incl. element elimination (isotropic + materials). The data may be used to describe the plastic behavior of isotropic + materials in non-linear analysis, such as crash simulations. The input is defined + according to the needs of Material 103 (single stress strain option) in the + PAM-CRASH explicit Finite Element code, but can also be used for equivalent material + laws in alternative simulation environment (see PAM-CRASH Solver Reference Manual., + Material 103). + + + + + + + + + + + + + + + + This type describes the plasticity curve of isotropic + materials + + + + ... + + Plastification curve incl. element elimination + (isotropic materials) + + Plastification curve incl. element elimination (isotropic + materials) The data may be used to describe the plastic behavior of + isotropic materials in non-linear analysis, such as crash + simulations. The input is defined according to the needs of Material + 103 (single stress strain option) in the PAM-CRASH explicit Finite + Element code, but can also be used for equivalent material laws in + alternative simulation environment (see PAM-CRASH Solver Reference + Manual., Material 103) + Source: PAM-CRASH V2010 - Notes Manual + + + + + + + + + + + + Name of the post failure definition + + + + + + + Description of the post failure + definition + + + + + + + Strain rate for following plastcity + curve [1/s] + + + + + + + + plasticEliminationStrain [-]; Plastic + strain for element elimination during + the non-linear analysis + + + + + + + + + + + + + + Point with global/local reference + + + PointAbsRel type, containing an xyz data triplet. Each + of the components is optional. The refType attribute defines, + whether coordinates are absolute in the global coordinate system + [absGlobal], absolute in the parent element's local coordinate + system [absLocal]. If the object does not have a + parent, only [absGlobal] is permitted. + + + + + + + + + + X-Component + + + + + Y-Component + + + + + Z-Component + + + + + + + + + + Absolute values in global coordinate system + + + + + Absolute values in local coordinate system (default) + + + + + + + + + + + + + + + Point with constraints + + + Point constraint type, containing an xyz data triplet. + + + + + + + + + + X-Component + + + + + Y-Component + + + + + Z-Component + + + + + + + + + + + + + List of 3D points, kept in three relative coordinate + vecors (rX, rY, rZ) + + + + This set of vectors contains an ordered list of points + for rX, rY, and rZ coordinates in the form of stringBased + Vectors. The x, y and z vector elements with the same index + specify a 3D point relative to a geometric segment. + + + + + + + + + + + + + + + + + + + + Vector of rX coordinates. Relative + circumferential coordinate on wing, fuselage or nacelle profile + + + + + + Vector of rY coordinates. Relative span + coordinate along a segment + + + + + Vector of rZ coordinates. Relative coordinate + normal to the linear strake (normalised with chordlength / + diameter c*) + + + + + + + + + + + + + List of points + + + PointList type, containing an ordered list of points + + + + + + + + + + + Data point + + + + + + + + + + + + + List of points in x,y + + + PointList type, containing an ordered list of points + + + + + + + + + + + Data points in x-y-space. + + + + + + + + + + + + + List of 2D points, kept in two coordinate vecors (x, y) + + + + This set of vectors contains an ordered list of points + for x and y coordinates in the form of stringBased Vectors. + The x and y vector elements with the same index specify a 2D + point. The coordinates of the x vector of [0, 1]. + + + + + + + + + + + Vector of x coordinates + + + + + Vector of y coordinates + + + + + + + + + + + + + List of 3D points, kept in three coordinate vecors (x, + y, z) + + + + This set of vectors contains an ordered list of points + for x, y and z coordinates in the form of stringBased Vectors. + The x, y and z vector elements with the same index specify a 3D + point. + + + + + + + + + + + Vector of x coordinates + + + + + Vector of y coordinates + + + + + Vector of z coordinates + + + + + + + + + + + + + + Constraints + + + + Constraint settings for the point performance definition + + + + + + + + + + + Calibrated airspeed [m/s] + + + + + + + Mach number [-] + + + + + + + Climb angle [deg] + + + + + + + Rate of climb [m/s] + + + + + + + Rate of turn [deg/s] + + + + + + Thrust setting for derated engine as fraction of max. thrust (e.g.: for powered descents, deceleration not at IDLE, manoevres) + + + + + + + Rate of velocity [m/s^2] + + + + + + + Duration [s] + + + + + + + Angle of attack [deg] + + + + + + + Constant altitude [m] + + + + + + + + + + + + + + Point performance definitions + + + List of point performance definitions + + + + + + + + + + + + + + + + + + + pointPerformanceType + + + Specific performance settings for the point performance calculation (e.g.: a cruise Mach number) + + + + + + + + + + Name + + + + + Description + + + + + + + Defines at which part of the mission + the point performance should be + considered - after indicated segment + of the mission as defined in + performanceCase + + + + + + + Defines at which part of the mission + the point performance should be + considered - at the defined + massFraction within the mission as + defined in performanceCase + (mCurrent/mTO) + + + + + + + Defines at which part of the mission + the point performance should be + considered - at the defined + fuelFraction within the mission as + defined in performanceCase + (mFuelCurrent/mFuelTO) + + + + + + + + Indicates the type of point performance + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Requirements + + + + Requirement settings for the point performance definition + + + + + + + + + + + Sustained load factor to be achieved + + + + + + + Instantaneous load factor to be achieved + + + + + + + Specific excess power to be achieved [m/s] + + + + + + + Roll rate to be achieved [deg/s] + + + + + + + Roll acceleration to be achieved upon control onset [deg/s^2] + + + + + + + Roll acceleration to be achieved upon control stop [deg/s^2] + + + + + + + + + + + + + + Point: x,y,z + + + Point type, containing an xyz data triplet. + + + + + + + + + + X-Component + + + + + Y-Component + + + + + Z-Component + + + + + + + + + + + + + + Point: x + + + Point type, containing a x data. + + + + + + + + + + X-Component + + + + + + + + + + + + + + Point: x,y + + + Point type, containing an xy data doublet. + + + + + + + + + + X-Component + + + + + Y-Component + + + + + + + + + + + + + + Point: x,y,z + + + Point type, containing an obligatory xyz data triplet. + + + + + + + + + + X-Component + + + + + Y-Component + + + + + Z-Component + + + + + + + + + + + + + + Point: x, z + + + Point type, containing an xz data doublet. + + + + + + + + + + X-Component + + + + + Z-Component + + + + + + + + + + + + + + Point: y + + + Point type, containing a y data. + + + + + + + + + + Y-Component + + + + + + + + + + + + + + Point: y, z + + + Point type, containing an yz data doublet. + + + + + + + + + + Y-Component + + + + + Z-Component + + + + + + + + + + + + + + Point: z + + + Point type, containing a z data. + + + + + + + + + + Z-Component + + + + + + + + + + + + + + Positive double values larger than 0 + + + + + + + + + + + + + + + + + Positive integer values larger than 0 + + + + + + + + + + + + + + + + + Vector with semicolon separated positive integer values + + + + Any positive integer values separated by semicolons are permitted, e.g.: + +<intVectorTest>0;1;2;3;4;5</intVectorTest> + + +<intVectorTest>1</intVectorTest> + + +<intVectorTest>0,1,2,3,4,5</intVectorTest> + + +<intVectorTest>0.;1.;2.</intVectorTest> + + +<intVectorTest>-1;0;1</intVectorTest> + + + + + + + + + + + + + + + + + + + Positionings of the wing. + + + Positionings type, containing all the positionings of + the wing sections. + + + + + + + + + + + + + + + + + + + Positioning of the wing section + + + + The positionings describe an additional translation of + sections. Basically, the positioning is a vector having the + length 'length' and an orientation that is described by the + parameters 'sweepAngle' and 'dihedralAngle'. If the 'sweepAngle' + and the 'dihedralAngle' are set to zero (or left blank) the + positioning vector equals the positive y-axis of the coordinate + system (in case of a positive 'length'). + If the parameter 'fromSectionUID' is set, the + positioning describes the translation between the 'from' towards + the 'to' section. If the parameter 'fromSectionUID' is left + blank the origin of the positioning vector is the origin of the + parent coordinate system. + The origin of the section coordinate system is the + position which is described by the positioning vector PLUS the + translation which is described in the section. + Please note: If the origin of the positioning vector is + defined by using another section, i.e. fromSection is defined, + the origin of this vector equals the end of the positioning + vector of the previous section. This means that the section + translation of the from-section has no influence on the + positioning of the to-section. Therefore the total translation, + which is described by positionings, is the sum of the current + positioning and all positionings that are defined 'before'. + + An example for this is given at positioning 3 and 4 at + the picture below. Please note, that any other combination of + positionings would be possible. + Application of the sweepangle does not lead to a + rotation of the section. Application of the dihedral does not + lead to a rotation of the section. + + + + + + + + + + + + + + Name of the positioning. + + + + + Description of the positioning. + + + + + + Distance between inner and outer section + (length of the positioning vector). + + + + + Sweepangle between inner and outer section. + This angle equals a positive rotation of the positioning vector + around the z-axis of the wing coordinate system. + + + + + + Dihedralangle between inner and outer section. + This angle equals a positive rotation of the positioning vector + around the x-axis of the wing coordinate system + + + + + + Reference to starting section of the + positioning vector. If missing, the positioning is made from the + origin of the wing coordinate system. + + + + + Reference to ending section (section to be + positioned) of the positioning vector. + + + + + + + + + + + + + + Specification of the power breakdown case + + + + + + + + + + + + + Altitude + + + + + + + + Mach number + + + + + + + Calibrated air speed + + + + + + + True air speed + + + + + + + + + + UID of global flight point at cpacs/vehicles/flightPoints/flightPoint + + + + + + + + Configuration + + + + + + + + + + + + + + Power breakdowns + + + + + + + + + + + + + + + + + + + + Specification of the power breakdown case + + + + + + + + + + UID of the corresponding trajectory + + + + + + + + + + + + + Power flow + + + + + + + + + + + Name + + + + + + + Description + + + + + + + UID of the system architecture connection + + + + + + + + + + + + + + Power flow + + + + + + + + + + + + + + + + + + + + + + Power flow + + + + + + + + + + + + + + + + + + + + + + pressureBulkheadAssemblyPositionType + + + PressureBulkheadAssemblyPosition type, containing a + pressure bulkhead assembly position + + + + + + + + + + Frame to which bulkhead is attached to + + + + + + UID of bulkhead element description + + + + + + + + + + + + + + + pressureBulkheadAssemblyType + + + PressureBulkheadAssembly type, containing pressure + bulkhead assemblies + + + + + + + + + + + + + + + + + + + pressureBulkheadsType + + + PressureBulkheads type, containing pressure bulkheads + + + + + + + + + + + + + + + + + + + + pressureBulkheadType + + + PressureBulkhead type, containing data of a pressure + bulkhead + + + + + + + + + + Name of the pressure bulkhead structural + element + + + + + Description of the pressure bulkhead + structural element + + + + + UID of structural sheet element used for the + bulkhead + + + + + Choice between flat and curved bulkhead types + + + + + additional data for flat (forward) pressure + bulkhead + + + + Number of vertical reinforcements on flat + bulhhead + + + + + UID of structural elements used as vertical + reinforcements + + + + + Number of horizontal reinforcements on flat + bulhhead + + + + + UID of structural elements used as + horizontal reinforcements + + + + + + additional data for curved (rear) pressure + bulkhead + + + + Radius of bulkhead calotte in the plane of + the adjacent frame + + + + + maximum flection of the pressure bulkhaed + calotte + + + + + Number of radial reinforcements (equally + distributed) on curved bulhhead + + + + + UID of structural elements used as radial + reinforcements on curved bulkheads + + + + + + + + + + + + + + + + structuralElementType + + + profileBasedStructuralElements type, containing a list + of profile based structural elements + + + + + + + + + + + + + + + + + + + Structural elements based on profiles + + + + + Short description + + The ProfileBasedStructuralElement type containins the + data of a structural element, that are based on 2-dimensional profiles. + + There are three approaches to model profile based structural elements: + + by specifying global beam properties + by referencing a structuralProfile2D element + by choosing one of the prescribed standard profiles + + + + + + 1. Global beam properties + + + In the section + globalBeamProperties + the properties + of the structural profile in an equivalent beam representation + are defined. + + + + + 2. Structural 2D profile + + + The + structuralProfileUID + element refers to the + uID + of the + structuralProfile2D + element. + As described in the corresponding documentation, this profile is defined by several points in the x-y-space. + Two points always form a sheet. + The properties of each sheet are defined in the + sheetProperties + element. + The orthotropy direction of composite materials equals the sheets' x-axis. + The orthotropy direction angle equals a positive rotation around the sheets' z-axis as indicated in the picture below (part 3), which shows an example of a wing stringer.: + + + + + + + + 3. Standard structural 2D profile + + + Instead of referencing a + structuralProfile2D + element, it is also possible to select a predefined standard profile. + These profiles are listed in the figure below. + Under + sheetProperties + , only the + standardProfileSheetID + (equals S1, S2, ...) must now be specified along with a corresponding length. + + + + + + + + + + + + + + + + + Name of the profile based structural element + + + + + + Description of the profile based structural + element + + + + + Choice between global beam properties and sheet properties + + + + + + Choice between general profile element + description (referencing a structuralProfile) and predefined + standard profiles + + + + Definition based on structuralProfile + definition + + + + Reference to the structural profile profile + uID + + + + + + Reference point in structural profile + definition for structural element definition + + + + + + + Standard Profile Type, see picture below for + further information. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + profileGeometry2DType + + + + A profile is defined by a profile name, an optional + description and a 2-dimensional pointlist with both + coordinates mandatory. All point coordinates are transferred + to the global coordinate system depending on the context they + are used in. The points have to be ordered in a mathematical + positive sense. The x-coordinates of the profile has to be + normalized between 0 and 1. First and last point + may, but need not to, be identical. Hence, it is possible to + include "open" profiles. However, the trailing edge position of + the upper and lower point need to be identical. No crooked + trailing edges are possible. + Example 1: For a conventional nacelle profile, the airfoil + coordinates are defined in x and y. The points have to be ordered + from the trailing edge along the lower side to the leading + edge and then along the upper side back to the trailing edge. + When used for a nacelle the profile axis align + with the global axes as follows: + +x_profile -> +x_global; + +y-profile -> -z_global + Example 2: For a fuselage, the coordinates are + also given in x and z with x as the normalized fuselage height. + Starting point of the profile should be the lowest point + (typically in the symmetry plane), then upwards on the positive x-side up to the highest + point (again, typically in the symmetry plane). Depending on, + whether the fuselage shall be specified with symmetry condition + or not, the profile either ends there, or continues on the + negative x-side back down to the lowest point. + Alternatively, it is possible to specify the + coordinates of a profile via the CST (class function /shape + function transformation technique) notation. Please see the + cst2DType for further information. + A profile can be symmetric. In that case the profile + is interpreted as being not closed and will be closed by + mirroring it on the symmetry plane. + + + + + + + + + + + Name of profile + + + + + Description of profile + + + + + + + + + + + + + + + + + + + + + + + + + + + + profileGeometryType + + + + A profile is defined by a profile name, an optional + description and a 3-dimensional pointlist with all three + coordinates mandatory. For typical profiles, one of the + coordinate vectors contains only "0" entries. All point + coordinates are transferred to the global coordinate system. The + points have to be ordered in a mathematical positive sense. + Normalized coordinates are not required. First and last point + may, but need not to, be identical. Hence, it is possible to + include "open" profiles. However, the trailing edge position of + the upper and lower point need to be identical. No crooked + trailing edges are possible. + Example 1: For a conventional wing, the airfoil + coordinates are defined in x and z with all the y-coordinates + set to "0". The points have to be ordered from the trailing edge + along the lower side to the leading edge and then along the + upper side back to the trailing edge. + Example 2: For a fuselage, the coordinates are + typically given in y and z with x set to "0". Starting point of + the profile should be the lowest point (typically in the symmetry + plane), then upwards on the positive y-side up to the highest + point (again, typically in the symmetry plane). Depending on, + whether the fuselage shall be specified with symmetry condition + or not, the profile either ends there, or continues on the + negative y-side back down to the lowest point. + Alternatively, it is possible to specify the + coordinates of a profile via the CST (class function /shape + function transformation technique) notation. Please see the + cst2DType for further information. + A profile can be symmetric. In that case the profile + is interpreted as being not closed and will be closed by + mirroring it on the symmetry plane. + + + + + + + + + + + Name of profile + + + + + Description of profile + + + + + + + + + + + + + + + + + + + + Profiles + + + Profiles type, containing profile geometries + + + + + + + + + + + + + + + + + + + + + + + + + + Attachments of the pylon to the parent. + + + + + + + + + + + + + + + + + + + + + + + Attachment of the pylon to the parent. + + + + + + + + + + + + + Material properties of the attachment. + + + + + + Link to the structural profile of the + attachment. + + + + + + UID of the attachment. + + + + + + + + + + + + Structural properties of the pylon box (ribs, upper, + lower and side panels). + + + + + + + + + + + + + + + + + + + UID of the pylon box. + + + + + + + + + + + + Definition of pylon pins. + + + + + + + + + + + + + + + + + + + + + + Definition of one pylon pin. + + + + + + + + + + + + + First element (parentAttachmentUID, engineUID + or uID of a pylon structure. + + + + + Second element (parentAttachmentUID, engineUID + or uID of a pylon structure. + + + + + Position of the pylon pin related to the pylon + coordinate system. + + + + + + Blocked DOFs. Refers to the rotated + coordinate system that is defined in 'orientation'. + + + + + + + + UID of the pin. + + + + + + + + + + + + Structural properties of all tibs of the engine pylon + box. + + + + + + + + + + + + + + + + + + + + + + Definition of a rib set. + + + + RibDefinitionType, containing the definition for ribs. + Ribs are defined in sets of one or more ribs. The positions of + the rib, as well as the orientation of the ribs are defined in + 'ribPositioning'. The cross section properties, as e.g. + materials, are defined in 'ribCrossSection'. + + + + + + + + + + + Name of the rib set. + + + + + Description of the rib set. + + + + + + + + + + + + + + + + + pylonRibsPositioningType + + + + Within the ribsPositioning type the position and the + orientation of the ribs of the rib set are defined. + The forward and the rear beginning of the rib set is + defined using relDepthStart and relDepthEnd. The orientation of + the ribs is defined in ribRotaton. The number of ribs of the + current rib set is either defined by ribNumber or by spacing. + + + + + + + + + + + + relDepthStart defines the forward location of + the beginning of the rib set. 0 equals the forward end of the + pylon box, while 1 equals the rear end of the pylon box. + + + + + + relDepthEnd defines the rear end. 0 equals the + forward end of the pylon box, while 1 equals the rear end of the + pylon box. + + + + + Ribs can be rotated in the side view. The + defaults to 90°, which equals an orientation along the pylons + z-axis. The angle is measured around the positive y-direction + of the pylon. + + + + + + The spacing of the ribs defines the distance + between two ribs, measured along the pylons x-axis. First rib + is placed at relDepthStart. + + + + + RibNumber defines the number of ribs in this + ribSet. First rib is at relDepthStart along the pylons x-axis, + last rib is at relDepthEnd. The spacing is constant. + + + + + + + + RibCrossingBehaviour can either be "cross" or + "end". If it is end then ribs will end it they intersect + another rib. It it is cross ribs are placed uncut. + + + + + + + + + + + + + + + + + + + + + Structural properties of pylon shackles (for pylon to + parent attachment), if existing. + + + + + + + + + + + + + + + + + + + + + + + Structural properties of a pylon shackle. + + + + + + + + + + + + + Material properties of the shackle. + + + + + + Link to the structural profile of the shackle. + + + + + + + UID of the shackle. + + + + + + + + + + + + Structural properties of the pylon shells. + + + + + + + + + + + + + + UID of the structural profile. + + + + + + Material settings. + + + + + + UID of the structure. + + + + + + + + + + + + Definition of the load carrying structure of the engine + pylon. + + + + + + + + + + + + + + + + + + + + + + + + + + + + Structural properties of struts (drag struts, upper + links and tangent links), if existing. + + + + + + + + + + + + + + + + + + + + + + + + radiativeForcingType + + + + + + + + + + + + + + + + + + + + + + + + + + + + Rectangle + + + + The width of the profile is always 1, since scaling is performed after referencing it (e.g., in the fuselage). + The resulting profile is defined by the following equation: + + + + + with + c = cornerRadius + and + r = heightToWidthRatio + . + + + Example: Rectangle with + cornerRadius + =0.125 and + heightToWidthRatio + =0.5 + + + + + + + + + + + + + + + + + + + Corner radius + + + + + + + + + + + + + + + + + + Height-to-width ratio + + + + + + + + + + + + + + + + recurringCostType + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Reference values + + + Reference type, containing the reference values of the + aircraft model + + + + + + + + + + Reference area (typically planform area) + + + + + + Reference length (typically Mean Aerodynamic + Chord MAC). In CPACS, only one reference length exists (and is + used, e.g. for all three moment coefficients. Coordinates given + relative to MAC shall always use this length as MAC. + + + + + + Moment reference point (in global coordinate + system). The x-coordinate is typically chosen same as of the + leading edge of the wing in the spanwise section having a + chordlength identical to MAC. Coordinates given as %MAC shall + always use this x-coordinate and length (e.g. 0%MAC = x, 100%MAC + = x + length). The y coordinate is typically 0. The z coordinate + is often chosen either as 0., or as z of fueselage nose or as z + of middle of center fuselage part. + + + + + + + + + + + + + + + + + + + + + + + + + + + Released stores + + + + + + + + + + + + + + + + + + + + + + + + Released store + + + + + + + + + + + + + + + + uID of the released store(s). + + + + + + + Quantity of released stores + + + + + + + + + + + + + + Remaining contributions to aerodynamic coefficients + + + + This node lists the remaining contributions which were not specified so that the sum of the coefficients are equal to the total coefficients. + + + + + + + + + + + + + + + + + + + + Remaining contribution to aerodynamic coefficients + + + + This node lists a remaining contribution which was not specified so that the sum of the coefficients are equal to the total coefficients. + + + + + + + + + + + + Name + + + + + + + Description + + + + + + Type (numerical/unspecified): "numerical", for example, describes rounding errors to clearly + separate them from other effects currently labelled as "unspecified". + The latter usually summarizes physical effects such as viscosity and should be further described via "description". + The approach is currently being tested in practice in order to derive a robust definition of categories in the future. + + + + + + + + + + + + + + + + + + + + + + + + Requirement classification based on the MoSCoW method (must, should, could or wont) + + + + + + + + + + + + + + + + + + + + requirementType + + + + + + + + + + + + + + + + + + + + + + + RibIdentificationType, defining one rib. + + + + + + + + + + + + + UID of the rib definition set. + + + + + + Number of the rib of the rib definition set. + + + + + + + + + + + + + + Definition of the rib rotation + + + The rotation around z describes the rotation around the + wings midplane normal axis. The defaults to 90°. The reference + for the 'zero-angle' of the z-rotation is defined in + ribRotationReference. + + + + + + + + + + RotationReference defines the reference for + the z-rotation it is either sparUID, „LeadingEdge“, + „TrailingEdge“, "globalX", "globalY" or "globalZ". + If it is not defined the rotation reference is + the eta-axis (=leading edge, that is projected on the wings + y-z-plane). A z-rotation angle of 90 degrees means, that the rib + is perpendicular on the ribRotationReference (e.g. spar, leading + edge...). The rib itself is always straight, and the rotation + is defined with respect of the intersection point of the rib + with the ribRotationReference. + + + + + The rotation around z describes the rotation + around the wings midplane normal axis. The defaults to 90°. The + reference for the 'zero-angle' of the z-rotation is defined in + ribRotationReference. + + + + + + + + + + + + + rivetJointAreaAssemblyPositionType + + + RivetJointAreaAssemblyPosition type, containing a rivet + joint area assembly position + + + + + + + + + + + + + + + + + + + + + rivetJointAreasAssemblyType + + + RivetJointAreasAssembly type, containing rivet joint + area assemblies + + + + + + + + + + + + + + + + + + + rivetsType + + + Rivets type, containing rivets + + + + + + + + + + + + + + + + + + + rivetType + + + Rivet type, containing a rivet + + + + + + + + + + Name of the rivet type + + + + + Description of the rivet type + + + + + + Tensile Strength of the rivet type + + + + + + Shear Strength of the rivet type + + + + + + + + + + + + + + + Rotation curve + + + + + The figure below shows an example of a rotation curve. + Together with the corresponding XML code, the definition is explained in more detail. + + + + + + First, the reference system is defined via + referenceSectionUID + , for which in this example the section with + uID="engine_nacelle_fanCowl_section1" + is referenced. + This in turn contains a + transformation + (not shown here), for example a translation by + z=0.4 + and a scaling, where the + x + -direction is stretched by a factor of two. + + + The rotation curve is now described in this reference system. + It is predefined in the profile library and referenced via a its + uID + . + Note that the curve is defined in the range + x=[0,..,1] + in order to be reasonably transformed by the reference system. + + + Next, the blending from the rotated profile of the nacelle segment to the rotation curve is defined. + The corresponding start and end points are given in curve coordinates + zeta + of the corresponding profiles. + Note that the lower part of the segment profile counts from + zeta=[-1,..,0] + and the upper part counts from + zeta=[0,..,1] + . + In between, the blending is linear. + + + + engine_nacelle_fanCowl_section1 + fanCowl_upperSection + -0.6 + -0.5 + -0.2s + -0.1 + + ]]> + + + + Fan cowl rotation curve profile + + 0;0.5;1 + -0.1;-0.2;-0.05 + + + ]]> + + + + + + + + + + UID of the section which serves as reference + + + + + Start zeta [-1,..,1]; relative curve coordante along the rotation curve from which it will be inserted in the nacelle. + + + + + End zeta [-1,..,1]; relative curve coordante along the rotation curve up to which it will be inserted in the nacelle. + + + + + Start zeta for blending [-1..1]; relative curve coordinate along the nacelle profile at which blending from the nacelle profile to the rotation curve will begin. + + + + + End zeta for blending; relative curve coordinate along the nacelle profile at which blending from the rotation curve to the nacelle profile will end. + + + + + UID of the rotation curve profile; the profile should be defined in x=[0..1] to be transformed by the section which is referenced by referenceSectionUID. + + + + + + + + + + + + rotorAirfoilsType + + + RotorAirfoils type, containing rotor airfoil + geometries. See profileGeometryType for further documentation + + + + + + + + + + + + + + + + + + + + rotorBladeAttachmentsType + + + RotorBladeAttachments type, containing all hinges and + blade UIDs attached to the current rotor hub. + + + + + + + + + + + + + + + + + + + rotorBladeAttachmentType + + + RotorBladeAttachment type, defining the elements used + to attach one or more rotor blades to the rotor head. + + + + + + + + + + Name of the blade attachment. + + + + + + Description of the blade attachment. + + + + + + + The azimuthAngles element is used to specify + a list of discrete azimuth angles (in deg) at which instances + of attached blades are to be created. The number of blades will + equal to the number of elements of the vector. E.g. + <azimuthAngles>0;90;180;270</azimuthAngles> for a + four blade rotor with equal equiangularly distributed blades. + The transformation of the respective rotor blade corresponds to + a rotation by azimuthAngle around the z axis of the rotor + coordinate system in mathematically positive sense of rotation. + + + + + + If only the number of blades is specified, + the attached blades will be distributed equiangularly and the + first blade will be attached at azimuth angle 0. (Formula: + azimuthAngle[i] = i*360deg/numberOfBlades, + i=0..numberOfBlades-1) + + + + + + Definition of all hinges used to attach the + rotor blade. + + + + + UID of the rotorBlade which should be attached + to the rotor hub. + + + + + + + + + + + + + + rotorBladesType + + + + RotorBlades type, containing all the rotor blade + gometry definitions of an rotorcraft model. + Rotor blade geometries are defined using the same data + structure as wings (wingType). But in order to be compatible + with the other rotor blade related types (e.g. rotorType, + rotorHubType, rotorHubHingeType) there are some additional + conventions/requirements regarding the definition and + orientation of rotorBlade geometries: + + Rotor blades should be positioned relative to the + global z-axis the way they will be positioned to the rotor + shaft (when blade azimuth=0deg). + The global x-axis should be used as radial axis + (usually the quarter chord line of the rotor blade coincides to + a great extent with the x-axis of the rotor blade coordinate + system). + All sections should be positioned in the positive + x halfspace. + Segments should connect sections with ascending x + coordinates. + Airfoils defined in the rotorAirfoils node should + be used instead airfoils from the wingAirfoils node. + + + + + + + + + + + + + + + + Rotor blade geometries are defined using the + same data structure as wings (wingType). But in order to be + compatible with the other rotor blade related types (e.g. + rotorType, rotorHubType, rotorHubHingeType) there are some + additional conventions/requirements regarding the definition and + orientation of rotorBlade geometries: see remarks. + + + + + + + + + + + + + + rotorcraftAnalysesType, results from several analysis + modules connected to CPACS + + + RotorcraftAnalyses type, containing detailed analysis + data of the rotorcraft + Within this element results from analysis modules are + stored that rely to the overall definition of the rotorcraft. + These include e.g. aerodynamic data or loadCases + For further documentation please refer to the + respective elements. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + rotorcraftGlobalType + + + RotorcraftGlobalType type, containing global data of + the rotorcraft + + + + + + + + + + Number of passenger seats + + + + + Cargo transport capacity [kg] + + + + + + Cruise Mach Number + + + + + Configuration of the rotorcraft: + standard(single main rotor, single tail rotor) / tandem / + coaxial/intermeshing / sideBySide/tiltRotor/tiltWing + + + + + + + + + + + + + + massBreakdownType + + + + + 1. General + + + The + massBreakeDown + is subdivided in + designMasses + , + fuel + , + payload + and + mOME + (operating empty mass). + + + designMass + + The design mass is a description from TLARs and can + be understand as design criteria. + + fuel + and + payload + + The fuel and payload mass are the maximum masses + which can be achieved. Full fuel tanks, all passengers on + board and full cargo holding. + + mOEM + + + The operation empty mass structure is based on the Airbus Mass + Standard brake down [AIRBUS MASS STANDARD 2008]. The + operator’s mass empty (OME) is defined by the sum of the + following component masses: + + operator’s items + manufacturer’s mass empty (MME) + + + + + + + 2. massDescription + + + Each sub component has the following + massDescription + which include a: + + Name + Description + parentUID + Mass value + Mass location + Mass orientation + Mass Inertia. + + + + That + massdescription + can be found at the + designMasses + direct under each item. At the + fuel + , + payload + and + mOME + under massDescription in each item and sub item. + + + + For the clean up the + mOME + there is consisting a script witch is programmed in Matlab but + also as standalone vision available. Setting for that tool can + be done under + toolspesifics/cmu + . + + + + + + + + + + + + + + + + + + + + + + + + + Mass + + + + + + + + + + + + + Manufacturer empty mass description + + + + + + + + + + + + + + + + + Mass + + + + + + + + + + + + + Group mass of hierarchy level 1 + + + + + + + + + + + + + + + Mass + + + + + + + + + + + + + Group mass of hierarchy level 2 + + + + + + + + + + + + + + + Operating empty mass + + + + + + + + + + + + + Operating empty mass description + + + + + + + + + + + + + + + + rotorcraftModelType + + + RotorCraftModel type, containing a complete rotorcraft + model (Geometry and all specific data). The rotorcraftModelType + is basically a copy of the aircraftModelType with the following + additional elements: rotors, rotorBlades, driveSystems. + Furthermore the following elements have been adapted for + rotorcraft: global and analyses (aeroPerformance and + massBreakdown). + + + + + + + + + + Name of rotorcraft model + + + + + Description of rotorcraft model + + + + + + + + + + + + + + + + + + + + + + + + + + Rotorcraft + + + Rotorcraft type, containing all the rotorcraft models. + + Most of the extensions used in the rotorcraft type have + been defined as part of the work in the DLR project RIDE + (Rotorcraft Integrated Design and Evaluation, 2009-2012). + Therefore some of the definitions and conventions are tightly + coupled to the RIDE toolchain and tools. Further generalization + and assimilation of these parts to the definitions for fixed-wing + aircraft is planned for the near future. + + + + + + + + + + + + + + + + + + + Rotor blade elements + + + + RotorBlades type, containing all the rotor blade + gometry definitions of an rotorcraft model. + Rotor blade geometries are defined using the same data + structure as wings (wingType). But in order to be compatible + with the other rotor blade related types (e.g. rotorType, + rotorHubType, rotorHubHingeType) there are some additional + conventions/requirements regarding the definition and + orientation of rotorBlade geometries: + + Rotor blades should be positioned relative to the + global z-axis the way they will be positioned to the rotor + shaft (when blade azimuth=0deg). + The global x-axis should be used as radial axis + (usually the quarter chord line of the rotor blade coincides to + a great extent with the x-axis of the rotor blade coordinate + system). + All sections should be positioned in the positive + x halfspace. + Segments should connect sections with ascending x + coordinates. + Airfoils defined in the rotorAirfoils node should + be used instead airfoils from the wingAirfoils node. + + + + + + + + + + + + + + + + Rotor blade geometries are defined using the + same data structure as wings (wingType). But in order to be + compatible with the other rotor blade related types (e.g. + rotorType, rotorHubType, rotorHubHingeType) there are some + additional conventions/requirements regarding the definition and + orientation of rotorBlade geometries: see remarks. + + + + + + + + + + + + + + Rotor blade + + + + + + + + + + Name of the wing. + + + + + Description of the wing. + + + + + + + + + + + + + + + + + + + Rotor + + + + + + + + + + + + + + + + + + + Rotor type, containing a rotor (main rotor, tail rotor, + fenestron, propeller,...) of an rotorcraft model. + + + + Rotor type, containing a rotor (e.g. main rotor, tail + rotor, fenestron, propeller,...) definition of a rotorcraft + model. + The position and attitude of the rotor is defined + using the transformation element. The following image shows the + CPACS conventions for the orientation of rotors and rotor axis + systems: + + + + + The origin coincides with the center of rotation. + + The z-axis corresponds to the axis of rotation + and thus coincides with the rotor shaft centerline. It Points + in the main thrust direction of the rotor (usually upwards for + a main rotor, forwards for a propeller). + The x-axis points from nose to tail (usually + rearwards for main and tail rotors, upwards for a propeller). + + The y-axis completes the right-handed orthogonal + coordinate system. + + Rotor hub attributes, hinges and references to + attached rotor blades are defined in the rotorHub element. + + + Note that rotor blade geometries are only referenced and not + defined in the child nodes of the rotor element. Refer to the + documentation of rotorBladesType ( + Empty#T/rotorBladesType + ) and wingType ( + Empty#T/wingType + ) for information on the definition of rotor blade geometries. + + The following figure shows the transformations to be + applied to rotorBlade geometries to visualize them in the rotor + frames for a given state (each rotor: rotorAzimuth given, each + hinge: hingeDeflection given): + + + + + + + + + + + + + + Name of the rotor. + + + + + Description of the rotor. + + + + + Nominal value of the angular rotation speed in + rotations per minute (rpm). + + + + + The rotorHub element contains the definition + of the rotor hub type and number and azimuth angles of the + attached blades and their hinges. The rotor hub position and + attitude coincides with the rotor axis system's origin and z + axis. + + + + + + + + + + + + + + + Rotor elements + + + + + + + + + + + + + + + + + + + + rotorHubHingesType + + + RotorHubHinges type, defining hinges used to attach a + rotor blade to the rotor head. + + + + + + + + + + Definition of a flap, lead-lag or pitch hinge. + + + + + + + + + + + + + + rotorHubHinge type, containing a rotor hub hinge + (flap/leadLag/pitch). + + + + RotorHubHinge type, containing a rotor hub hinge + (flap/leadLag/pitch) of a rotorcraft model. + + + + + + + + + + + Name of the hinge. + + + + + Description of the hinge. + + + + + + Hinge type. Possible values: "flap", "pitch" + "leadLag". This is used to define the rotation axis of the hinge + (flap = y-axis in blade cs, pitch = x-axis in blade cs, lead-lag + = z-axis in blade cs). + + + + + + + + + + + + The angle (in deg) at which the hinge is in + neutral position. This element is normally used to define + precone or prelag angles of the attached blade. Defaults to 0. + + + + + + Static stiffness of the hinge in (N/m) for + linear hinges and (N.m/deg) for angular hinges. Default value: + +inf (statically rigid hinge) + + + + + Dynamic stiffness of the hinge in (N/m) for + linear hinges and (N.m/deg) for angular hinges. Default value: + +inf (statically rigid hinge) + + + + + Damping of the hinge in (N/(m/s)) for linear + hinges and (N.m/(deg/s)) for angular hinges. Default value: +inf + + + + + + + + + + + + + + + rotorHubType + + + RotorHub type, containing definitions for the rotor hub + and attached hinges and blades. + + + + + + + + + + Name of the rotor hub. + + + + + Description of the rotor hub. + + + + + + Rotor head type. Possible values: "semiRigid", + "rigid", "articulated", "hingeless" + + + + + + + + + + + + + Rotor blade attachments are used to define how + many rotor blades are attached at which azimuth positions of the + rotor hub and the used hinges. + + + + + + + + + + + + + + rotorsType + + + Rotors type, containing all the rotors (mainRotors, + tailRotors, fenestrons, propellers, ...) of an rotorcraft model. + + + + + + + + + + + + + + + + + + + + Rotor type, containing a rotor (main rotor, tail rotor, + fenestron, propeller,...) of an rotorcraft model. + + + + Rotor type, containing a rotor (e.g. main rotor, tail + rotor, fenestron, propeller,...) definition of a rotorcraft + model. + The position and attitude of the rotor is defined + using the transformation element. The following image shows the + CPACS conventions for the orientation of rotors and rotor axis + systems: + + + + + The origin coincides with the center of rotation. + + The z-axis corresponds to the axis of rotation + and thus coincides with the rotor shaft centerline. It Points + in the main thrust direction of the rotor (usually upwards for + a main rotor, forwards for a propeller). + The x-axis points from nose to tail (usually + rearwards for main and tail rotors, upwards for a propeller). + + The y-axis completes the right-handed orthogonal + coordinate system. + + Rotor hub attributes, hinges and references to + attached rotor blades are defined in the rotorHub element. + + + Note that rotor blade geometries are only referenced and not + defined in the child nodes of the rotor element. Refer to the + documentation of rotorBladesType ( + Empty#T/rotorBladesType + ) and wingType ( + Empty#T/wingType + ) for information on the definition of rotor blade geometries. + + The following figure shows the transformations to be + applied to rotorBlade geometries to visualize them in the rotor + frames for a given state (each rotor: rotorAzimuth given, each + hinge: hingeDeflection given): + + + + + + + + + + + + + + Name of the rotor. + + + + + Description of the rotor. + + + + + UID of the part to which the rotor is mounted + (if any). The parent of the rotor can e.g. be the fuselage. In + each rotorcraft model, there is exactly one part without a + parent part (The root of the connection hierarchy). + + + + + + Rotor type. Possible values: "mainRotor" + (default), "tailRotor", "fenestron" or "propeller".. + + + + + + + + + + + + + + Nominal value of the angular rotation speed in + rotations per minute (rpm). + + + + + Transformation (scaling, rotation, + translation). This element is used to define the position and + attitude of the rotor relative to the global or the parent + component's axis system. Note that an anisotropical scaling + transformation should not be applied to the rotor. + + + + + + The rotorHub element contains the definition + of the rotor hub type and number and azimuth angles of the + attached blades and their hinges. The rotor hub position and + attitude coincides with the rotor axis system's origin and z + axis. + + + + + + + + + + + + + + + runwayILSType + + + RunwayILS type, containing ILS data of a runway + + + + + + + + + + + Position of the localizer antenna + + + + + + + Position of the glide slope antenna + + + + + + Angle of the glide path + + + + + + + + + + + + + + Runway start position + + + + + Description of the vehicle on the runway relative to the runway threshold. + + + + + + + + + + + + + + X-position in cartesian coordinates in the runway coordinate system + + + + + + + Y-position in cartesian coordinates in the runway coordinate system + + + + + + + Z-position in cartesian coordinates in the runway coordinate system + + + + + + + + + Lengthwise distance along the runway centerline from the runway threshold + + + + + + + Lateral offset from the runway centerline. Positive values on the starboard side. + + + + + + + + + + + + + + + runwaysType + + + Runways type, containing data of the airport's runways + + + + + + + + + + + + + + + + + + + + runwayType + + + Runway type, containing data of a runway + + + + + + + + + + Name of runway + + + + + Description of runway + + + + + Position in degrees north + + + + + Position in degrees east + + + + + Threshold elevation + + + + + Runway heading + + + + + Takeoff run available + + + + + Landing distance available + + + + + Conditions of the runway + + + + + + + + + + + + + + + Seat elements + + + Seat element collection type + + + + + + + + + + Seat element for use in the decks + + + + + + + + + + + + + Seat element + + + Seat element type, containing the base elements of the cabin + + + + + + + + + + Number of seats + + + + + + + + + + + + + Seat modules + + + Seat module instance collection type. + + + + + + + + + + Seat module + + + + + + + + + + + + + shaftLinkedComponentsType + + + ShaftLinkedComponents type, containing UIDs of engines, + transmissions and rotors linked by a shaft. + + + + + + + + + + + UID of a linked engine. + + + + + UID of a linked transmission shaft input. + + + + + + UID of a linked transmission shaft output. + + + + + + UID of a linked rotor. + + + + + + + + + + + + + + shaftsType + + + Shafts type, containing all the shafts of a drive + system. + + + + + + + + + + + + + + + + + + + shaftType + + + Shaft type defining a shaft used as a link between + drive system components. + + + + + + + + + + + + + + + + + + + + + + sheet3DType + + + + + + + + + + + + + + + + + + + + + + + + + sheetBasedStrcuturalElementsType + + + sheetBasedStrcuturalElementsType, containing sheet + based structural element definitions + + + + + + + + + + + + + + + + + + + sheetBasedStructuralElementType + + + sheetBasedStructuralElementType type, sheet definition + for use in fuselage/structure + + + + + + + + + + Material definition of the skin segment + (Material, thickness, (lay-up)) + + + + + + + + + + + + + + sheetList3DType + + + + + + + + + + + + + + + + + + + + + + List of sheets, connecting 2-dimensional profile + points. + + + SheetList type, containing a list of sheets. Each sheet + combines two points to one sheet. + + + + + + + + + + + + + + + + + + + sheetPointsType + + + + + + + + + + + + + + + + + + + + + + sheetType + + + Sheet type, containing connection data of a sheet + + + + + + + + + + + Name of sheet within the profile definition + + + + + + Description of sheet within the profile + definition + + + + + Point from which the sheet definition starts + start + + + + + Continuity definition for profile geometry + generation. 0= C0 (allows sharp edges, default), 1= C1 (defines + tangential continuity), 2= C2 (defines curvature continuity) + 2=all + + + + + + + + + + + + + + Definition of an orientation vector at P1 + + + + + + Point at which the sheet definition ends + + + + + + Continuity definition for profile geometry + generation. 0= C0 (allows sharp edges, default), 1= C1 (defines + tangential continuity), 2= C2 (defines curvature continuity) + 2=all + + + + + + + + + + + + + + Definition of an orientation vector at P2 + + + + + + + + + + + + Side strut(s) (Assumption: one end of the strut will connect to the main strut and the other end will be given as endPoint) + + + + + + + + + + + + Sidewall panel elements + + + Sidewall panel element collection type + + + + + + + + + + Sidewall panel element for use in the decks + + + + + + + + + + + + + Sidewall panels + + + Sidewall panel instance collection type. + + + + + + + + + + Sidewall panel + + + + + + + + + + + + + + singleGenericMassType + + + + + + + + + + + + + + + + + + + + + + Skid landing gears + + + List of skid gears + + + + + + + + + + + + + + + + + + + fuselageSkinSegmentType + + + FuselageSkinSegment type, containing material on skin + over circumference + + + + + + + + + + + + + + + + + + + fuselagePanelType + + + FuselagePanel type, panel of the fuselage between + stringers/ frames (new in V1.5) + + + + + + + + + + UID of sheetBasedStructuralElement used for + the panel + + + + + UID of frame at start of the skin segment + + + + + + UID of frame at end of the skin segment + + + + + + UID of stringer at start of the skin segment + + + + + + UID of stringer at end of the skin segment + + + + + + + + + + + + + + + skinType + + + Containing data defining the skin + + + + + + + + + + Default UID of sheetBasedStructuralElement + used for the fuselage skin not covered by individual panels + + + + + + + + + + + + + + + Source / Target + + + + + + + + + + + UID of a component defined under aircraft(rotorcraft)/model + + + + + + UID of a sub-component + + + + + + + External element (ambient | passengers), which is not explicitly defined in CPACS. + External elements indicate that this is an element relevant to modeling the system, but is not itself contained in the system. + + + + + + + + + + + + + + + Source / target system according to ATA chapter + + + + + + UID of another systemArchitecture + + + + + + + + + + + + + + SparCells of current spar. + + + sparCells are an optional Element. They are defined via + the etaCoordinates and define a region of special cross section + and material properties. + + + + + + + + + + + + + + + + + + + Spar cell of the spar. + + + + Within spar cells a special area of the spar is + defined where different cross section and material properties + shall be defined. + The area of the spar is defined by using the + parameters 'fromEta' and 'toEta'. The definition of the caps, + webs and rotation is equivalent to the cross section definition + of the complete spar. + + + + + + + + + + + Beginning (= inner border) of the spar cell. + + + + + + Ending (= outer border) of the spar cell. + + + + + + Upper Cap + + + + + + Lower Cap + + + + + + Web 1 + + + + + + Web 2 + + + + + + The angle between the wing middle plane and + web 1 [deg]. Default is 90 degrees. Positive rotation is around the + spar axis heading along with the positive eta-axis. + + + + + + + + + + + + + + + Definition of the spar cross section. + + + + Spar type, containing the cross section definition of + a spar. The spar middle point is defined by the intersection of + the wing middle plane and web1. This equals the coordinate + defined within the sparPosition. + Please find below a picture where all spar cross + section parameters as well as the orientation references for + the material definition can be found: + + + + + + + + + + + + + + + + + + + The angle between the wing middle plane and + web1. Default is 90 degrees. Positive rotation is around the + intersection axis of the spar and the wing middle plane. The + positive heading of this axis is inline with the positive + heading of the componentSegment eta-axis. + + + + + + + + + + + + + Spar definition points on the wing. + + + + sparPositionType, a sparPostion defines a location + within the componentSegment where a spar in mounted. Eta and xsi + are relative to the componentSegment. + Please find below a picture for an example definition + of 3 spars in one wing, by using spar position points and spar + segments: + + + + + + + + + + + + + + + + + + + + + + + Spar position on the wing + + + + sparPositionType, a sparPostion defines a location + within the componentSegment where a spar in mounted. Eta and xsi + are relative to the componentSegment. + Please find below a picture for an example definition + of 3 spars in one wing, by using spar position points and spar + segments: + + + + As an alternative to the relative eta coordinate it is + possible to specify an elementUID so that the spar position is + relative to the outer geometry, e.g. kink, of the wing. + + + + + + + + + + + + Defines a spar position on an existing rib using a relative xsi coordinate + to determine the chord wise position on that rib + + + + + Defines a spar position using relative eta/xsi coordinates + + + + + Defines a spar position via a point on a curve + + + + + + + + + + + + + + sparPositionUIDs of the spar. + + + + sparPositionType, a sparPostion defines a location + within the componentSegment where a spar in mounted. Those + positions are combined to spars by using a list of spar position + uIDs. The order of the sparPositionUIDs must be the same as the + order of the points on the real spar (from root to tip or from + tip to root). + Please note: orientation of a spar must be always + outbound or always inbound. A zigzag spar orientation where + e.g. the spar starts at the root, goes to the tip and goes back + to another point at the root is not allowed. + Please find below a picture for an example definition + of 3 spars in one wing, by using spar position points and spar + segments: + + + + + + + + + + + + + + List of spar position uIDs. + + + + + + + + + + + + + + Spar segments of the wing. + + + sparSegmentsType, containing multiple sparSegment + (=spars) of the wing. + + + + + + + + + + + + + + + + + + + SparSegments (=spars) of the wing. + + + SparSegmentType, each spar is defined by multiple + sparPositions that are referenced via their uID. The spar cross + section is defined in 'sparCrossSection'. + + + + + + + + + + Name of the spar segment (=spar). + + + + + + Description of the spar segment (spar). + + + + + + + + + + + + + + + + + Species + + + + + + + + + + Share + + + + + + + + + + + + + + + + + + + + Species type + + + + + + + + + + + + + + + + + + List of segment uIDs to which the configuration is to be applied + + + + + + + + + + + + + + + + + + + + + + + + Specification of a segment uID and index of the parameter lapses + + + + + + + + + + + + + + + + UID of the segment for which the specific configuration holds. + + + + + + + Vector with semicolon separated indices of the parts of the respective segment within the mission definition for which the specific configuration setting holds. Example: scheduling configurations for a climb or descent segment (different settings of moveables and gears) on altitudes/velocities + + + + + + + + + + + + + + Specific configuration uIDs + + + + + + + + + + + + + + + + + + + + + + + + Connection between segments, pointPerformances and a configurationUID + + + + + + + + + + + + + + + + Configuration uID + + + + + + + + List of pointPerformanceUIDs + + + + + + + + + + + + + + Specific heat map, containing the specific heat capacity of a material at different temperatures. + + + The specific heat of a material can vary with the temperature. The vectors specificHeat and temperature + must have the same size to be valid. The data should be linearly interpolated. + + + + + + + + + + + Temperature in [K] + + + + + Specific heat capacity of the material in [J/(kg*K)] + + + + + + + + + + + + + specificPerformanceMapsType + + + Collection of all assignments of specific performance maps to selected mission segments + + + + + + + + + + + + + + + + + + + Specific performance map + + + + + Applying a specific performance map to selected mission segments. In addition to the obligatory + defaultPerformanceMapUID + at least a + segmentUID + or + pointPerformanceUID + must be given. + + + + + + + + + + + + UID of performance map to be used for mission segments + + + + + + + List of all mission segment UIDs to which the performance map is to be applied + + + + + List of point performance UIDs to which the performance map is to be applied + + + + + + List of point performance UIDs to which the performance map is to be applied + + + + + + + + + + + + + + Speed designators + + + + Provides an enumerated list of V-speeds as defined by regulations. + + + + + + + + + + + Design maneuvering speed + + + + + + + Design speed for maximum gust intensity + + + + + + + Design cruise speed, used to show compliance with gust intensity loading + + + + + + + Design diving speed, the highest speed planned to be achieved in testing + + + + + + + Designed flap speed + + + + + + + Stall speed or minimum steady flight speed for which the aircraft is still controllable + + + + + + + Stall speed or minimum flight speed in landing configuration + + + + + + + Stall speed or minimum steady flight speed for which the aircraft is still controllable in a specific configuration + + + + + + + Minimum control speed + + + + + + + Never exceed speed + + + + + + + Maximum operating limit speed + + + + + + + + + + + + + Sphere + + + + + + + + + + Radius [m] + + + + + + + + + + + + + Definition of the wings spoilers. + + + Definition of the wings spoilers. + + + + + + + + + + + + + + + + + + + Spoilers of the wing. + + + A spoiler is defined via its outerShape relative to the + componentSegment. The WingCutOut defines the area of the upper + skin that is removed by the spoiler. Structure is similar to the + wing structure. The mechanical links between the spoiler and the + parent are defined in tracks. The deflection path is described + in path. Additional actuators, that are not included into a + track, can be defined in actuators. + + + + + + + + + + Name of the spoiler. + + + + + Description of the spoiler. + + + + + + UID of the parent of the spoiler. The parent + is the componentSegment, where the spoiler is attached. + + + + + + + + + + + + + + + + + + + + + Standard profile + + + + + + + + + + + + + + + + + + + + + + + State parameters list + + + Contains a list of all state parameters. + + + + + + + + + + + + + + + + + + + + State parameter definition + + + Contains the values of a parameter and its uid as reference. + + + + + + + + + + + + + + + + + + + + + + + + Static power breakdowns + + + + + + + + + + + + + + + + + + + Static power breakdown case + + + + + + + + + + Name + + + + + Description + + + + + + + + + + + + + + + + stiffnessType + + + + + + + + + + + + + + + + + + + + + + + + + + + Stored chemical energies + + + + + + + + + + + + + + + + + + + Stored chemical energy + + + + + + + + + + + + + Fill factor + + + + + + + + + + + + Fill factor reference (optimalVolume | usableVolume | realVolume) + + + + + + + + + + + + + + + + + + + + + + + Stored electrical energy + + + + + + + + + + + Charge level + + + + + + + + + + + + + + + + + + + + + Stored electric energies + + + + + + + + + + + + + + + + + + + stringArrayBaseType + + + Base type for string array nodes (including maptype + array attribute) + + DEPRECATED: As of CPACCS version 3.3, the + mapType + attribute is set to optional to ensure the compatibility of older data records. However, since the type is uniquely defined via the XSD, the attribute is superfluous and will therefore be completely omitted in future versions. + + + + + + + + + + + + + + + + + + stringBaseType + + + Base type for string nodes (including external data + attributes) + + + + + + + + + + + + + + + + + + + stringerFramePositionType + + + + Description of individual stringer / frame positions + + + + + + + + + + + + + + UID of profile based structural element + + + + + + + x position in absolute value + + + + + + UID reference to a fuselageSectionElement + + + + + + + y coordinate of reference system + + + + + + z coordinate of reference system + + + + + + angle definition to calculate intersection + with loft + + + + + + Continuity definition for profile extrusion: + 0= C0 (allows sharp edges, default), 2= C2 (defines curvature + continuity) + + + + + + + + + + + + + Definition of interpolation between different + profiles: 0= no interpolation 1= interpolation of structural + profile + + + + + + + + + + + + + + + + + + + + + + + framePositionUIDs of the frame + + + + + A framePostion defines a location where a frame in mounted. + + + + + + + + + + + framePositionUID of the frame, where the landing gear + is attached to. + + + + + + + + + + + + + stringersAssemblyType + + + StringersAssembly type, containing an assembly of + stringers (new V1.5) + + + + + + + + + + + + + + + + + + + arbitraryStringerType + + + ArbitraryStringer type, containing stringer definition + (CPACS V1.5+) + + + + + + + + + + + + + + + + + + + + stringUIDBaseType + + + This is the base type that links to other components. It should always contain a UID. + This node has an additional attribute isLink that will be used if a stringBaseType refers to a uID. TIXI can then + perform automatic validation for the existence of the referenced uID. + Furthermore this node contains an additional attribute symmetry. The symmetry attribute may take three values: symm, def, full + def: The element refers to the geometric component that has a symmetry attribute and refers only to the defined side of the geometric component. + symm: The element refers to the geometric component that has a symmetry attribute and refers only to the symmetric side of the geometric component. (Similar to the previous _symm solution) + full: The element refers to the geometric component that has a symmetry attribute and refers to the complete component. (This is the default behaviour) + + + + + + + + + + DEPRECATED + : The + isLink + attribute is set to optional to ensure the compatibility of older data records. However, since the linking character is explicitly defined by the + stringUIDBaseType + , the attribute is superfluous and will therefore be completely omitted in future versions. + + + + + + + + + + + + + + + + + + + + + + stringVectorBaseType + + + + Base type for string vector nodes + The vector base type can include optional uncertainty + information. The description of uncertainties is placed in + additional attributes. First, it is described by an attribute that + describes the type of uncertainty function called functionName. + The functionName attribute includes the tag name of the + distribution function which is listened in the table shown below. + Each uncertainty function is further describes by a set of + parameters that are described in the table below. + If the uncertainty values change for the elements of + the vector than the attribute may be written as a list of values + separated by semicolons + + DEPRECATED: As of + CPACS + version 3.3, the + mapType + attribute is set to optional to ensure the compatibility of older data sets. + However, since the type is uniquely defined via the XSD, the attribute is superfluous + and will therefore be completely omitted in the next major release (Note: requires + TiXI >= 3.3). Please contact the + CPACS + team + if for any reason you see a long-term need for the + mapType + attribute. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Structural elements + + + structuralElements Type, containing the different structural + elements + + + + + + + + + + + + + + + + + Seat elements (Deprecation warning: This element will soon be removed from the official CPACS. Use the new seat modules located at cpacs/vehicles/deckElements!) + + + + + + + + + + + + + + + Structural mount + + + + + + + + + + + + + + If this value is set to true then only the end points of the intersection shall be included as nodes in the model. + + + + + + The UID for the first connection UID may include for wings: skin, sparUID, ribDefinitionUID, ribNumber, stringerUID, stingerNumber, and for fuselages: skinSegmentUID, frameUID, stringerUID, crossBeamUID, crossBeamStrutUID, longFloorBeamUID. + + + + + + Optional counter to specify numbered items, e.g. ribs in a ribSet. + + + + + + The UID for the second connection UID may include for wings: skin, sparUID, ribDefinitionUID, ribNumber, stringerUID, stingerNumber, and for fuselages: skinSegmentUID, frameUID, stringerUID, crossBeamUID, crossBeamStrutUID, longFloorBeamUID. + + + + + + Optional counter to specify numbered items, e.g. ribs in a ribSet. + + + + + + + + + + + + + + + structuralProfile3DType + + + + + + + + + + + + + + + + + + + + + + + + + + Definition cross sections of structural profiles. + + + + Structuralprofiles type, containing cross section + information of structural profiles. + + + + + + + + + + + + + + + + + + + + 2-dimensional cross sections of structural profiles. + + + + + StructureProfile type, containing data of a structure + profile cross sections. The cross section profile is defined by + several points (->pointList) in the x-y-space. Two points are + combined to one sheet (->sheetList) by using the pointUIDs. + + This profile is defined by several points in the + x-y-space. Always two points are combined to one sheet. The + properties of each sheet are defined in the 'sheetProperties' + section by referencing on the sheetUID and the material + properties. The orthotropy direction of composite materials equals + the x-sheet axis. The orthotropy direction angle equals a positive + rotation around the z-sheet axis as indicated in the picture below + (part 3.), where a wing stringer is defined as an example: + + + + + + + + + + + + + + + Name of the structure profile. + + + + + + Description of the structure profile. + + + + + + List of structural profile points, only x and + y. + + + + + + + + + + + + + + + + Structural wall reinforcement definition specifying physical properties of a fuselage wall segment. + + + + + + + + + + + + + + Reference to a sheet element definition specifying the physical properties of the wall's shell. + + + + + Reinforcements running along the position polygon of the wall positions. + + + + + Reinforcements running in lateral/radial direction in the wall segment plane. + + + + + Reinforcement at inner side of wall. This is either, depending on the extrusion direction flag, the edge of the wall that connects the positions ("positiveDirection") or the edge of the wall where the wall intersects with the fuselage skin in the opposite direction of the extrusion direction. + + + + + + Reinforcement at outer side of wall. The outer side of the wall is defined as the edge of the wall at the intersection of the wall with the fuselage skin running along the main direction of the wall. + + + + + + + Lateral caps are the reinforcements of + the wall at the edges lateral to the + main direction of the wall. These caps + can be either defined at start, end, + start and end or at all wall positions + according to the placement flag. + + + + + + + + + + + + + + + Strut assembly + + + Geometric description, spatial placement and specification of material parameters + + + + + + + + + + Strut properties + + + + + The starting point of the support strut must connect to the main strut. This element specifies the relative position on the main strut (0 -> top end, 1 -> bottom end). + + + + + + + + + + + + End position in absolute coordinates. Coordinates are relative to parent if it has a parentUID reference (otherwise global). + + + + + End position in eta/xsi/relHeight coordinates + + + + + End position as a relative position on another strut of this landing gear + + + + + + Attachment to an aircraft wing or fuselage component + + + + + Reference to an actuator uID + + + + + + + + + + + + + + + Strut properties + + + + + Geometric description and material properties + of a strut + + + + + + + + + + + + + (Outer) radius of the strut + + + + + + Material of the strut + + + + + Inner radius of the strut + + + + + + + + Reference to structural element for a more + detailed cross section definition + + + + + + + + + + + + + + + Geometric description and material properties of a strut + + + + + + + + + + Length of the strut + + + + + + + + + + + + + + Design study parameters and results + + + + Contains optimization data such as definitions of design parameters and design studies. + + + + + + + + + + + + + + + + + + + + + + + + + subFleetsType + + + Contains a list of different sub fleets + + + + + + + + + + + + + + + + + + + subFleetType + + + Each fleet can be divided into sub fleet groups + + + + + + + + + + Name of fleet + + + + + Description of the fleet + + + + + A ; separated list of all tailsign strings + + + + + + + + + + + + + + subLoadType + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Superellipse + + + + A profile based on superellipses is composed of an upper and a lower semi-ellipse, which may differ from each other in their parameterization. The total width and height of the profile is always 1, since scaling is performed after referencing (e.g., in the fuselage). + + This + lowerHeightFraction + describes the portion of the lower semi-ellipse on the total height. + + The resulting profile is defined by the following set of equations: + + + + + + + with + + + + The following examples indicate the various possibilities of parametric profiles: + + Example 1 + : ( + mUpper,nUpper,mLower,nLower, lowerHeightFraction + ) = (0.5; 2; 5; 3; 0.25) + + + + + + Example 2 + : ( + mUpper,nUpper,mLower,nLower, lowerHeightFraction + ) = (2; 2; 2; 2; 0.5) = a circle + + + + + + Example 3 + : ( + mUpper,nUpper,mLower,nLower, lowerHeightFraction + ) = (1; 1; 1; 1; 0.5) = a square / diamond + + + + + + Note + : For exponents that are infinitely large, the superellipse converges to a rectangle. However, the value + Inf + is not a valid entry at this point. Use the + square + element instead. + + + + + + + + + + + + Exponent m for upper semi-ellipse + + + + + Exponent n for upper semi-ellipse + + + + + Exponent m for lower semi-ellipse + + + + + Exponent n for lower semi-ellipse + + + + + + Fraction of height of the lower semi-ellipse relative to the total height + + + + + + + + + + + + + + + + + + + + Main landing gear support beam + + + + Definition of the main landing gear support beam, if a + support beam is used for the attachment. The definition includes + cross section properties as well as the position of the support + beam. + + + + + + + + + + + + + + + + + + + + Symmetry (see CPACS root node documentation for details) + + + + + + + + Symmetry inheritance from parent element disabled + + + + + Symmetry inherited from parent element (default behavior, i.e. also applies if attribute not set) + + + + + Symmetry w.r.t. the x-y plane of the CPACS coordinate system + + + + + Symmetry w.r.t. the x-z plane of the CPACS coordinate system + + + + + Symmetry w.r.t. the y-z plane of the CPACS coordinate system + + + + + + + + + + + System architectures + + + + + + + + + + + + + + + + + + + System architecture + + + + + + + + + + Name + + + + + Description + + + + + ATA Chapter | generic + + + + + + + + + + + + + + + + Connections + + + + + + + + + + + + + + + + + + + Connection + + + + + + + + + + Name + + + + + Description + + + + + Type of the connection. + + + + + + + + + + + + + + + + + + + + + + + + + + + + Control devices + + + + + + + + + + Control function indicating the activation state + + + + + + + + + + + + + + System elements + + + + + + + + + + + + + + + + + + + + + + + + + + Control parameter definition for System or Connection state + + + + + + + + + + Control parameter indicating active state + + + + + Control parameter indicating inactive state + + + + + + + + + + + + + Systems + + + + Systems type, containing the aircraft's control system + data + Please see the attached picture for further + documentation + + + + + + + + + + + + + + Node for geometrical layout of system components + based on simple geometric shapes + + + + + + Cockpit controls, e.g. stickRoll, pedals + + + + + + Different commandCases that are commanded, + e.g. roll, accelerate + + + + + Control Distributors, deliver inputs to the + control actuators. E.g. different angles of different ailerons. + + + + + + Control laws, for regulated actuation + + + + + + + + + + + + + + + + + + tailplaneAttachmentAreaType + + + tailplaneAttachmentArea type, containing dat on + fuselage + structure to attach tailplaine + + + + + + + + + + Definition of tailplane attachment area + (Standard + Configuration) + + + + + type of tailplane attachment: Currently + restricted to + 'Type1' and 'Type2' (see documentation) + + + + + + + + + + + + + + Definitions of VTP interface + + + + + + Definitions of VTP interface + + + + + + + + + + + + + + + takeoffPerformanceParametersType + + + + + + + + + + + + + Take-off distance at liftoff speed VLOF. + + + + + + Take-off distance at safety speed V2. + + + + + + Optimal speed Velev at point of initiating + take-off rotation by elevator deflection for a minimum take-off + distance. + + + + + Optimal rotation speed VR for a mini-mum + take-off distance + + + + + Liftoff speed VLOF. + + + + + Safety speed V2. + + + + + Take-off decision speed V1 + + + + + Minimum control speed ground VMCG. + + + + + + Flight path angle being achieved at V2 with + one engine failure in 400 ft height above ground. This is the + result of a post trim calculation using the deter-mined V2. If + the trim calculation fails the entry is set to -90. + + + + + + + + + + + + + + Structural properties of the tangent links, if + existing. The tangent links do connect the engine pylon with the + engine to carry the thrust forces. + + + + + + + + + + + + + + + + + + + + + + simpleConnectionsType + + + SimpleConnections type, containing simple connections + + + + + + + + + + + + + + + + + + + + simpleConnectionType + + + SimpleConnection type, containing a simple connection + + + + + + + + + + + Can be each structural member (skinSegment, + stringer, frame, paxCrossBeam, cargoCrossBeam, + paxCrossBeamStrut, cargoCrossBeamStrut, long. floor beams, + floorPanel, seatModule) + + + + + Can be each structural member (skinSegment, + stringer, frame, paxCrossBeam, cargoCrossBeam, + paxCrossBeamStrut, cargoCrossBeamStrut, long. floor beams, + floorPanel, seatModule) + + + + + + + + + + + + + + timeBaseType + + + Base type for time nodes (including external data attributes) + This time type is based on the xsd:time definition. + "To specify a time zone, you can either enter a time in UTC time by adding a "Z" behind the time - like this: 09:30:10Z + or you can specify an offset from the UTC time by adding a positive or negative time behind the time - like this: + 09:30:10-06:00 + or + 09:30:10+06:00" (description taken from http://www.w3schools.com/xml/schema_dtypes_date.asp) + + + + + + + + + + + + + + + + + + + timeConstraintBaseType + + + + Base type for time nodes including a relational operator attribute indicating valid constraint region + The timeConstraintBaseType extends the timeBaseType and thus inherits all its attributes. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Toolspecific data + + + + This type contains a list of tools each specifying some basic tool information as well as the actual toolspecific part. + + The toolspecific elements must be defined in a separate namespace which can be specified and linked with the corresponding XSD file + in the CPACS header: + <cpacs xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" + xsi:noNamespaceSchemaLocation="pathToSchemaFile/cpacs_schema.xsd" + xsi:schemaLocation="http://www.cpacs.de/myTool pathToToolspecificSchemaFile/toolspecific_myTool.xsd"> + A simple example could look like this: + <toolspecific> + <tool> + <name>myToolName</name> + <version>1.2.3</version> + <myTool xmlns="http://www.cpacs.de/myTool" schemaVersion="1.0"> + <parentElement> + <childElement1>stringValue</childElement1> + <childElement2>1.0</childElement2> + </parentElement> + </myTool> + </tool> +</toolspecific> + + + + + + + + + + + + + + + + + + + + Tool identification + + + + Tool information as described in the toolspecificType. + + + + + + + + + + + + Name of the tool + + + + + + + Version of the tool + + + + + + + Wildcard for the root element of a toolspecific namespace + + + + + + + + + + + + + + topologyEntriesType + + + + + + + + + + + + + + + + + + + + + + topologyEntryType + + + A topology entry is used to combine the dynamic aircraft + models of several components, e.g. wing and fuselage. By default + these will be stiff. If desired stiffness and rotation with + respect to the CPACS coordinate system may be specified. + + + + + + + + + + + + + + + + + + + + + + + Torispherical dome + + + + + + + + + + R1: dish radius + + + + + R2: knuckle radius + + + + + + + + + + + + + totalOperatingCostType + + + + + + + + + + + + + + + + + + + + + + + + trackActuatorType + + + + + + + + + + + + + Reference to the uID of the actuator of the + track. + + + + + Definition of the material properties of the + actuator to track attachment. + + + + + + + + + + + + + + Joint coordinates + + + + Definition of a joint coordinates. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Specification of joint coordinates. + + + + Specification of joint coordinates. + + + + + + + + + + + + + + + + + + + + Set of joint coordinates + + + + Definition of a set of joint coordinates. + + + + + + + + + + + Value of the command parameter of a control distributor. If not given explicitly in the control distributor, linear interpolation between the neighboring points is required. + + + + + + + + + + + + + + + + + + + + + + + + wingSparsType + + + Spars type, a spar is defined by sparSegments that + stretch between multiple sparPositions + + + + + + + + + + + + + + + + + + + + + + + + + + + + Definition of the struts of a control surface track. + + + + Definition of the struts of a control surface track. + + + + + + + + + + + + + + + + + + + + Definition of a strut of a control surface track. + + + + Definition of a strut of a control surface track. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Definition of the wings trailing edge devices. + + + + Definition of the wings trailing edge devices. + + + + + + + + + + + + + + + + + + + + Trailing edge device of the wing. + + + A trailingEdgeDevice (TED) is defined via its + outerShape relative to the componentSegment. The WingCutOut + defines the area of the skin that is removed by the TED. + Structure is similar to the wing structure. The mechanical links + between the TED and the parent are defined in tracks. The + deflection path is described in path. Additional actuators, that + are not included into a track, can be defined in actuators. + + Leading and trailing edge are defined by the outer + shape of the wing segments, i.e. the trailing edge of a + trailingEdgeDevice is the trailing edge of the wing. This is also + valid for kinks that are present in the wing but not explicitly + modeled in the control surface. + The edges of the control surface within the wing are a + straight line in absolute coordinates! Hence, there needs to be a + straight connection between the eta-wise outer and inner points + of the edge that is within the wing in absolute coordinates. + + + + + + + + + + + Name of the trailing edge device. + + + + + + Description of the trailing edge device. + + + + + + UID of the parent of the TED. The parent can + either be the uID of the componentSegment of the wing, or the + uID of another TED. In the second case this TED is placed within + the other TED (double slotted flap). In this way n-slotted TEDs + can be created. + + + + + + + + + + + Definition of cruise rollers/mid-span stops. + Those features are small rolls at the leading edge of a flap + that keep the flap within the bending wing at cruise + configuration. + + + + + Definition of interconnection struts. Those + struts connect two neighbouring flaps and are load carrying in + case of an actuator of flap track failour. + + + + + Definition of z-couplings. Those elements + couple two neighbouring flaps in z-direction. + + + + + + + + + + + + + + + Trajectories + + + + + + + + + + + + + + + + + + + + + + Power breakdowns + + + + + + + + + + + + + + + + + + + Power breakdown case along a trajectory + + + + + + + + + + Name + + + + + Description + + + + + + + + + + + + + + + + trajectoryGlobalType + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + trajectoryType + + + + + + + + + + + + + + + + + + + + + + + + + + + 2D transformation + + + + + + + + + + + + + Scaling of the structural profile + + + + + + rotation around z-axis of profile definition + + + + + + translation of profile definition + + + + + + + + + + + + + + + Transformation + + + Transformation type, containing a set of + transformations. The order of the transformations is scaling + -> rotation -> translation, and they are executed in this + order. Any of them can be omitted; it will be replaced by its + defaults. + Transformations are always executed relative to the + child not the parent. I.e. a scaling does not have an influence + on the parent item. For example in the outer geometry of a wing + the element scaling does not influence the section. Scaling does + also not effect rotation and translation. + Scaling data default: 1,1,1. Those parameters + describe the scaling of the x-, y-, and z-axis. + Rotation data default: 0,0,0. The rotation + angles are the three Euler angles to describe the orientation of + the coordinate system. The order is always xyz in CPACS. + Therefore the first rotation is around the x-axis, the second + rotation is around the rotated y-axis (y') and the third + rotation is around the two times rotated z-axis (z''). + Translation data default: 0,0,0. Translations + can either be made absolute in the global coordinate system + (absGlobal) or absolute in the local Coordinate system (absLocal). + + + + + + + + + + + Scaling + + + + + Rotation + + + + + Translation + + + + + + + Rotation + + + + + Translation + + + + + + + Translation + + + + + + + + + + + + + + + Transformation + + + Transformation type, containing a set of + transformations. The order of the transformations is scaling + -> rotation -> translation, and they are executed in this + order. Any of them can be omitted; it will be replaced by its + defaults. + Transformations are always executed relative to the + child not the parent. I.e. a scaling does not have an influence + on the parent item. For example in the outer geometry of a wing + the element scaling does not influence the section. Scaling does + also not effect rotation and translation. + + + + + + + + + + Scaling data default: 1,1,1. Those parameters + describe the scaling of the x-, y-, and z-axis. + + + + + + Rotation data default: 0,0,0. The rotation + angles are the three Euler angles to describe the orientation of + the coordinate system. The order is always xyz in CPACS. + Therefore the first rotation is around the x-axis, the second + rotation is around the rotated y-axis (y') and the third + rotation is around the two times rotated z-axis (z''). + + + + + + Translation data default: 0,0,0. Translations + can either be made absolute in the global coordinate system + (absGlobal) or absolute in the local Coordinate system (absLocal). + + + + + + + + + + + + + + + transmissionGearRatioType + + + TransmissionGearRatio type, defining the ratio of + output rotation velocity to input rotation velocity. + + + + + + + + + + + + + + + + + + + + transmissionShaftInputsType + + + TransmissionShaftInputs type, defining the shaft inputs + of a transmission. + + + + + + + + + + + + + + + + + + + transmissionShaftInputType + + + TransmissionShaftInput type, defining a shaft input for + a transmission. + + + + + + + + + + + + + + + + + + + + transmissionShaftOutputsType + + + TransmissionShaftOutputs type, defining the shaft + outputs of a transmission. + + + + + + + + + + + + + + + + + + + transmissionShaftOutputType + + + TransmissionShaftOutput type, defining a shaft output + for a transmission. + + + + + + + + + + + + + + + + + + + + + transmissionsType + + + Transmissions type, containing all the + transmissions/gearboxes of a rotorcraft model. + + + + + + + + + + + + + + + + + + + transmissionType + + + Transmission type, defining a transmission/gearbox. + + + + + + + + + + + + + + + + + + + + + + + + + + Trim case + + + + + + + + + + + + + + Name + + + + + Description + + + + + UID of trim requirement + + + + + + + Description of the linear model + + + + + + + + + + + + + + Trim requirements + + + Contains a list of trim requirements + + + + + + + + + + + + + + + + + + + + Trim requirement + + + + + + + + Name + + + + + Description + + + + + UID of a predefined flight point + + + + + UID of weight and balance description + + + + + + + + + + + + + + + Trim + + + + Provides a list of trim cases + + + + + + + + + + + + + + + + + + + + Turbo generators + + + + + + + + + + + + + + + + + + + Turbo generator + + + + + + + + + + + + + + + UIDGroupDefinitionsType + + + + + + + + + + + + + + + + + + + + + + + UIDGroupDefinitionType + + + + + + + + + + + + + + + + + + + + + + + + + + + List of uIDs + + + + + + + + + + + Reference to a uID + + + + + + + + + + + + + + + + + + + + + Structural properties of the upper links, if existing. + The upper links do connect the upper forward part of the pylon + box with the forward wing attachment. + + + + + + + + + + + + + + + + + + + + + + List of segments that are allowed to be varied within a mission optimization. + + + + Provides a list of segments having variable conditions within the segmentBlock. + Example: a segmentBlock containing takeOff, climb, cruise, decent, landing segments has a cruise segment for which the range is variable. + The range of this segment is then to be calculated using the range defined for the segmentBlock while concerning the known ranges of all + other segments within the segmentBlock. + This concept needs to be practically tested. Does it suffice to mention (a list of) segments that are free to change to fit the overall block constraints? What happens if a segment is variable, though it has some constraints? When to define a segment as variable (climb until endPosition z, then endPosition x should be left free. Is the segment then variable? Probably not.). Somehow the 'free' segment should be in between fully defined segments (i.e.: a cruise+descent in between endPosition z == ICA and endPosition z == 0 for landing to define max range. How to define this exactly?) + + + + + + + + + + + + + + + + + + + variableSegmentType + + + + Containing the definition of variable segments for a segment block + + + + + + + + + + + defines uID of the segment having variable conditions + + + + + defines which condition(s) are variable within the segment (must be one of the defined + endConditions for the segmentBlock) + + + + + + + + + + + + + + + + + + + + System element + + + + + + + + + + Name + + + + + Description + + + + + + + + + + + + + + + + Vehicles + + + + + The + vehiclesType + contains all vehicle-specific + data. + + + This includes the vehicle itself (i.e. + aircraft + and + rotorcraft + ). Furthermore, components + (e.g. + engines + , + structuralElements + , etc.) + as well as physical properties of + materials + and + fuels + can be predefined for easy and consistent reuse via + uID + -references. + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Version Informations + + + + + + + + + + + + + + + + + + + Version Information + + + + + + + + + + CPACS version of the dataset + + + + + + Description of CPACS dataset + + + + + + Timestamp of initial CPACS dataset creation + + + + + + Creator of initial CPACS dataset + + + + + + + + + + + + + + + + vtpFrameDefType + + + Definition of the individual VTP attachments + + + + + + + + + + Definition of tailplane attachment area + (Standard Configuration) + + + + UID of the fuselage frame at this VTP + attachment + + + + + Flag for option for VTP attachment between + defined FrameUID and the next one + + + + + UID of panel element at VTP attachment (shell + elements) + + + + + UID of structural element at VTP attachment + (base, beams) + + + + + UID of structural element at VTP attachment + (horizontal, beams) + + + + + UID of structural element at VTP attachment + (radial, beams) + + + + + + + + + + + + + + vtpInterfaceDefType + + + Definition of the interface of the VTP + + + + + + + + + Definition of the VTP interface + + + + + Definition of the VTP attachment frames and + their + reinforcement + + + + + + Defines area for valid x-position of VTP (just + used + if attachmentpoint is directly based on frame) ==> check and + potentially warning message + + + + + + Definition of the max. distance between + fuselage and + the defined VTP pins ==> check and potentially warning + message + + + + + + Definition of reinforcement area at VTP frame + positions (relative coordinate, smaller than + 1.0) + + + + + + Definition of vertical reinforcements at VTP + frame + positions (relative coordinate, smaller than + 1.0) + + + + + + value to change from horizontal to radial + reinforcements for VTP frame plates + + + + + + UID of elements to connect VTP pins with + fuselage + (beam elements) + + + + + + + + + + + + Definition of wall positions to place walls inside fuselage. + + + + + + + Wall position definition specifying a point in the fuselage to be connected to a wall segment. + + + + + + + + + + Definition of a wall position to place walls inside fuselage. + + + + + + + UID of a bulkhead determining the + x-coordinate of the position with the given + y- and z-coordinates. + + + + + + + UID of a wall segment determining the + x-coordinate of the position with the given + y- and z-coordinates. + + + + + + + UID of fuselage section determining the + x-coordinate of the position with the given + y- and z-coordinates. + + + + + + Absolute x-coordinate of wall position in fuselage coordinate system. + + + + + + Absolute y-coordinate of wall position in fuselage coordinate system. + + + + + Absolute z-coordinate of wall position in fuselage coordinate system. + + + + + + + + + + + + Reference to wall position uID. + + + + + + + + + + + + + Wall segment definition. + + + + + + + + + + + + + Defines extrusion direction. Rotation angle + around fuselage x-axis of extrusion direction. A + value of 0deg means fuselage z-axis as extrusion + direction. Default: 0.0deg. + + + + + + + + + + + + + + By default, the wall is only extruded in positive direction. If doubleSidedExtrusion is true, the wall is additionally extruded in negative direction as well. Default: false. + + + + + Rotates the first edge of the wall segment so that it is adjacent with the structural element defined in the first wall position (bulkhead, fuselage section or another plane wall). Default: false. + + + + + Rotates the last edge of the wall segment so that it is adjacent with the structural element defined in the last wall position (bulkhead, fuselage section or another plane wall). Default: false. + + + + + + A list of uIDs referencing other + structural/geometric elements that shall serve + as a boundary of the wall element. Possible + references are floor, wall or + genericGeometryComponent. A major requirement is + that the referenced element has an intersection + with the wall for at least the distance between + two wall positions. So that a full geometric + face of the wall is bounded by it. Neighbouring + wall faces that are not completely bounded by + the reference element are not affected. + + + + + + + Reference to the structural property definition + of this wall segment. + + + + + + + List of wall position uIDs that are used for + this wall segment. At least two positions must + be defined (for start and end position of wall). + If more than two positions are referenced here, + the wall is constructed out of several planar + faces that connect two consecutive positions + (Note: Order of position uIDs defines + connectivity). + + + + + + + + + + + + + + + Definition of wall positions to place + walls inside fuselage. + + + + + + + List of wall segments. + + + + + + + + + + + + + + webType + + + + SparWeb type, containing the cross section area of the + spar web and the material properties. + Please find below a picture where all spar cross + section parameters as well as the orientation references for + the material definition can be found: + + + + + + + + + + + + + + Material definition of the spar web. + + + + + + relPos ranges from 0 to 1 It defines the + position of the web relative to the caps (see picture below).. + + + + + + + + + + + + + + weightAndBalanceCaseType + + + WeightAndBalanceCase type, containing weight and + balance data for one case + + + + + + + + + + + + + + + + + + + + + + + + + weightAndBalanceFuelInTanksType + + + + + + + + + + + + + + + + + + + + + + weightAndBalanceFuelInTankType + + + + + + + + + + + + + + + + + + Ranges from 0 for empty tank to 1 + + + + + + + + + + + + + + weightAndBalanceFuelType + + + + + + + + + + + + + + + + + + + + + + + + + weightAndBalancemCargosType + + + For a higher ganularity it is possible to add more + information on the actual Cargo that are included in the + operational case. Please note that the information needs to be + identical with the massBreakdown. Hence, only links via uIDs can + be specified. + + + + + + + + + + + + + + + + + + + + + + weightAndBalancemPaxxType + + + For a higher ganularity it is possible to add more + information on the actual Pax that are included in the + operational case. Please note that the information needs to be + identical with the massBreakdown. Hence, only links via uIDs can + be specified. + + + + + + + + + + + + + + + + + + + + + + weightAndBalancePayloadType + + + + + + + + + + + + + + + + + + + + + + + + + + Weight and balance + + + WeightAndBalance type, containing weight and balance + datasets + + + + + + + + + + + + + + + + + + + + Definition of the landing gear wheel. + + + The center plane of the wheel is located on the end point of the axle. + + + + + + + + + + Wheel radius + + + + + With of the wheel + + + + + Brake: false = + not braked; true = braked. + + + + + + + + + + + + + + windowAssemblyPositionType + + + WindowAssembly type, containing an the position of a + windows assembly + + + + + + + + + + UID of the window element to be used + + + + + + x position of window element on global x axis + + + + + + z position of window element reference point + + + + + + angle around global x axis to define window + position with respect to positionX and postionZ + + + + + + + + + + + + + + + windowsAssemblyType + + + WindowsAssembly type, containing an assembly of windows + + + + + + + + + + + + + + + + + + + + windowsType + + + Windows type, containing windows + + + + + + + + + + + + + + + + + + + + wingAeroPerformanceType + + + wingAeroPerformance type, containing performance maps + with aerodynamic data of a wing. + + + + + + + + + + Reference to the uID of the analysed wing + + + + + + References used for the calculation of the + force and moment coefficients of the wing (in the wing axis + system!) + + + + + Calculated aerodynamic performance maps of the + wing + + + + + + + + + + + + + wingAirfoilsType + + + WingAirfoils type, containing wing airfoil geometries. + See profileGeometryType for further documentation + + + + + + + + + + + + + + + + + + + Position of the landing gear on a wing + + + + Definition of the position of the landing gear + (intersection point of main strut and pintle sturt) on a wing, + using relative componentSegment coordinates + + + + + + + + + + Relative height of spar or rib at which landing gear is attached. + + + + + + Relative spanwise position (eta) of spar at which landing gear is attached. + + + + + Relative chordwise position (xsi) of the rib at which landing gear is attached. + + + + + + + + + + + + + Cells of the wing. + + + WingCells type, containing all the cells of the wing. + + + + + + + + + + + + + + + + + + + + Cell of the wing + + + + A cell defines a special region of the wing. Within + this region skin and stringer properties can be defined that + differer from the properties of the rest of the wing. In general + a cell is defined by defining four borders – the cell leading + and trailing edge and the inner border and the outer border. + Those borders can either be defined by using eta/xsi coordinates + or by referencing to spars and ribs. Mixed definitions (e.g. + forward border is defined due to a spar, side borders due to eta + coordinates) is allowed. In general a cell is quadrilateral. But + if e.g. the spar, which is used for the definition of the + trailing edge, has a kink, the cell can have more than four + corners. + The cell leading and trailing edge (= forward and rear + border) can either be defined by referencing to a spar + (->sparUID) or by the defining the xsi (=relative chord) + coordinates of the border (xsi1 = inner end; xsi2 = outer end). + + The cell inner and outer border can either be defined + by referencing to a rib (->ribDefinitionUID and ribNumber) or + by the defining the eta (=relative spanwise) coordinates of the + border (eta1 = forward end; eta2 = rear end). + Some examples for wing cells can be found in the + picture below: + + + + + + + + + + + + + + + + + + + + + + + + + + + + + Structure of the wing + + + wingComponentSegmentStructure type, containing the + whole structure (skins, ribs, spars...) of the wing. + + + + + + + + + + + + + + + + + + + + + + + + CutOuts of the wing + + + + + + + + + + + + + + + + + + + CutOut of the wing + + + + A wing cutout is defined using any combination of eta-xsi-spar-rib-uids. + It has the similar syntax to a wingCell. + + The cell leading and trailing edge (= forward and rear + border) can either be defined by referencing to a spar + (->sparUID) or by the defining the xsi (=relative chord) + coordinates of the border (xsi1 = inner end; xsi2 = outer end). + + The cell inner and outer border can either be defined + by referencing to a rib (->ribDefinitionUID and ribNumber) or + by the defining the eta (=relative spanwise) coordinates of the + border (eta1 = forward end; eta2 = rear end). + Some examples for wing cells can be found in the + picture below: + + + + + + + + + + + + + + + + + + Type of the cutout (upper|lower|both): upper shell, lower shell or both. + + + + + + + + + + + + + + + + + + + + + + + + Elements of the wing. + + + WingElements type, containing the elements of a wing + section. + + + + + + + + + + + + + + + + + + + Element of the section. + + + + Within elements the airfoils of the wing are defined. + Each section can have one or more elements. Within each element + one airfoil have to be defined. If e.g. the wing should have a + step at this section, two elements can be defined for the two + airfoils. + Mathematically spoken a element is a coordinate system + that is translated, rotated and scaled relative to the section + coordinate system. This transformation parameters are defined + within the transformation section. The wirfoil, which is linked + by using the parameter airfoilUID is directly 'copied' in the + element coordinate system. If e.g. the airfoil is defined from 0 + to 1 in x-direction and the total scaling of the elements x-axis + equals 3.5 the wing chord is 3.5 m long. + An example for wing element can be found in the + picture below: + + + + + + + + + + + + + + Name of the wing element. + + + + + Description of the wing element. + + + + + + Reference to a wing airfoil. + + + + + + + + + + + + + + + + Border of the fuel tank (either rib or spar). + + + + + + + + + + + + + + Spar uID of the bordering spar. + + + + + + + UID of the rib set of the bordering rib. + + + + + + RibNumber of the rib set of the bordering + rib. + + + + + + + + + + + + + + Definition of the geometry of the wing fuel tank by + defining a continouse list of borders. + + + + + + + + + + + + + + + + + + + + + + List of wing fuel tanks. + + + + + + + + + + + + + + + + + + + + + + Definition of one wing fuel tank. + + + + + + + + + + + + + Name of the wing fuel tank. + + + + + + Description of the wing fuel tank. + + + + + + + + + + + + + + + + + Definition of the wing-fuselage attachment. + + + Definition of the wing-fuselage attachment + + + + + + + + + + + + + + + + + + + Definition of the wing-fuselage attachment + + + + Definition of the wing-fuselage attachment. The area + of the fuselage attachment (resp. center wing box, CWB) is + defined by defining one resp. two ribs from the rib definition. + If one rib is defined (rib1) the CWB goes from the closer end of + the componentSegment (e.g. wing symmetry plane) to the defined + rib. If two ribs are defined (rib1 and rib2), the CWB is between + both ribs. + Additionally attachment pins can be defined. At those + positions the wing is attached to the fuselage. This can be e.g. + used for defining the wing-attachment of high wing + configurations, HTPs or VTPs. + + + + + + + + + + + Definition of first (=inner) rib of the + fuselage attachment. + + + + + Definition of the second (=outer) rib of the + fuselage attachment. Optional. Only to be used if attachment is + defined over two ribs. + + + + + Definition of position, orientation, materials + and blocked DOFs of attachment pins. + + + + + Definition of actuators (e.g. trim actuator of + an HTP) of the attachment. + + + + + + + + + + + + + wingInterfaceDefinitionsType + + + CenterFuselage high wing interface definitions + + + + + + + + + + + + + + + + + + + + + + + + + centerFuselageMainFramesType + + + High wing main frame definition, containing mainframe + UIDs + + + + + + + + + + + + + + + + + + + + + wingInterfaceSupportStrutsAssemblyType + + + wingInterfaceSupportStrutsAssembly type, containing + support struts assembly + + + + + + + + + + + + + + + + + + + + wingInterfaceSupportStrutType + + + wingInterfaceSupportStrut type, containing support + strut definition + + + + + + + + + + Name of support strut. + + + + + Type description: lateral or longitudinal + support strut. + + + + + + + + + + + + + + + + + + IntermediateStructure cells + + + Definition of the intermediateStructure of the + componentSegment of the wing. + + + + + + + + + + + + + + + + + + + Definition of the cell of the intermediateStructure + + + + + IntermediateStructure: + It defines the filling materials between the upper and + lower shell (e.g. honeycombe structures in a smeared + representation). IntermediateStructure is optional.The position + of the intermediateStructure is defined in so called cells (= + special areas on the wing). Default is no intermediateStructure. + + Material Definition of intermediateStructure: + + The material of the intermediateStructure is reference + by 'material'. The material orientation is defined by 'rotX' and + 'rotZ'. 'rotZ' is defined equivalent to the stringer angle resp. + the skin orthotropyDirection. 'rotX' equals a positive rotation + around the wings x-axis, while a rotation of zero is equivalent + to the wing middle plane. + A picture to clarify the reference direction of rotZ + (equivalent to orthothropy direction of the wing) can be found + in the picture below: + + + + Position definition by using cells: + A cell defines a special region of the wing. Within + this region the cell properties are defined. In general a cell + is defined by defining four borders – the cell leading and + trailing edge and the inner border and the outer border. Those + borders can either be defined by using eta/xsi coordinates or by + referencing to spars and ribs. Mixed definitions (e.g. forward + border is defined due to a spar, side borders due to eta + coordinates) is allowed. In general a cell is quadrilateral. But + if e.g. the spar, which is used for the definition of the + trailing edge, has a kink, the cell can have more than four + corners. + The cell leading and trailing edge (= forward and rear + border) can either be defined by referencing to a spar + (->sparUID) or by the defining the xsi (=relative chord) + coordinates of the border (xsi1 = inner end; xsi2 = outer end). + + The cell inner and outer border can either be defined + by referencing to a rib (->ribDefinitionUID and ribNumber) or + by the defining the eta (=relative spanwise) coordinates of the + border (eta1 = forward end; eta2 = rear end). + Some examples for wing cells can be found in the + picture below: + + + + + + + + + + + + + + + + + + Reference to the material of the intermediate + structure. + + + + + 'rotX' equals a positive rotation around the + wings x-axis, while a rotation of zero is equivalent to the wing + middle plane direction. + + + + + 'rotZ' is defined equivalent to the stringer + angle resp. the skin orthotropyDirection. + + + + + + + + + + + + + + Definition of a ribCell + + + RibCells are optional elements. They are defined via a + fromRib and a toRib. The enumeration is within the ribSet. + RibNumber 1 starts at etaStart. + + + + + + + + + + Defines the beginning of the ribCell. The + enumeration is within the ribSet. + + + + + Defines the ending of the ribCell. The + enumeration is within the ribSet. + + + + + WING: The Rotation along the x describes a + rotation around a line, that is defined by the intersection of + the rib with the wing middle plane (orientated from leading to + trailing edge). This angle defaults to 90° which means, that the + rib is perpendicular on the wings middle plane. PYLON: The + Rotation along the z describes a rotation around the pylons + z-axis (= rotation in top view). This angle defaults to 90° + which means, that the rib is perpendicular to the pylons x-axis. + + + + + + The orthotropyDirection is defined as rotation + around the ribs z-axis. The rib coordinate system is defined as + follows: x-axis is from leading to trailingeEdge of the + componentSegment in the direction of the rib elongation. z-axis + is normal to the rib in the direction of positive eta. y is + defined by right hand rule. Rotation is around the z-axis. Zero + degrees are at the x-axis positive direction. + + + + + + + + + + + + + + + + + Cross section properties of a wing rib + + + wingRibCrossSectionType, containing the definition of + ribsCrossSection + + + + + + + + + + The orthotropyDirection is defined as rotation + around the ribs z-axis. The rib coordinate system is defined as + follows: x-axis is from leading to trailingeEdge of the + componentSegment in the direction of the rib elongation. z-axis + is normal to the rib in the direction of positive eta. y is + defined by right hand rule. Rotation is around the z-axis. Zero + degrees are at the x-axis positive direction. + + + + + + WING: The Rotation along the x describes a + rotation around a line, that is defined by the intersection of + the rib with the wing middle plane (orientated from leading to + trailing edge). This angle defaults to 90° which means, that the + rib is perpendicular on the wings middle plane. The rotation + angle is defined at the intersection point of the rib with the + ribReference line. The rib itself is always straight and not + twisted. PYLON: The Rotation along the z describes a rotation + around the pylons z-axis (= rotation in top view). This angle + defaults to 90° which means, that the rib is perpendicular to + the pylons x-axis. + + + + + + + + Post element definition applied to all vertical intersections with spars + + + + + + + + + + + + + Explicit positioning of a wing rib + + + + Use this type for an explicit positioning of a rib. As opposed to + ribsPositioning, this defines a single rib connecting a specified start + and end point. + + + + + + + + + + + + + Defines the start of the rib defined in eta-xsi coordinates of a reference plane + + + + + + + Defines the start of the rib defined by a point on a reference curve + such as a spar, but not an explicit sparPosition + + + + + + + Defines the location of the beginning of the rib using a specific sparPosition. + + + + + + + + + Defines the end of the rib defined in eta-xsi coordinates of a reference plane + + + + + + + Defines the end of the rib given by a point on a reference curve + such as a spar, but not an explicit sparPosition + + + + + + + Defines the location of the end of the rib using a specific sparPosition. + + + + + + + + Defines the forward beginning of the ribs. It can either be a + sparUID or "trailingEdge" or "leadingEdge". + + + + + + + RibEnd defines the backward ending of the ribs. It can either be a + sparUID or "trailingEdge" or "leadingEdge". + + + + + + + + + + + + + + wingRibPointType + + + + The wingRibPointType is used to define reference points on ribs. + It can be used for rib set definitions (wingRibsPositioningType) as + well as explicit rib definitions (wingRibExplicitPositioningType). + + + + + + + + + + + + The UID of the rib definition. Can be a reference to nodes + of either wingRibsPositioningType or wingRibExplicitPositioningType. + + + + + + + For references of type wingRibsPositioningType this node indicates the rib number of the rib set. + If not given it defaults to 1. + + + + + + + Normalized xsi coordinate of the rib point which is measured along the rib + from the start point [0] towards the end point [1]. + + + + + + + + + + + + + + Wing ribs + + + RibDefinitions type, containing the definition of all + ribs of the wing. + + + + + + + + + + + + + + + + + + + Definition of a set of ribs + + + + RibDefinitionType, containing the definition for ribs. + Ribs are defined in sets of one or more ribs. The positions of + the rib, as well as the orientation of the ribs are defined in + 'ribPositioning'. The cross section properties, as e.g. + materials, are defined in 'ribCrossSection'. + + + + + + + + + + + Name of the rib set + + + + + Description of the rib set + + + + + + + + + + + + + + + + + + + + Positioning of a set of wing ribs + + + + The ribsPositioning type allows the definition of a set + of ribs which is distributed over a specified spanwise area. + The positions of the ribs are defined by placing the + ribs on a reference line on the wing (ribReference). The inner + and the outer beginning of the rib set is defined using etaStart + and etaEnd. The position of the forward and rear end of the ribs + is defined by ribStart and ribEnd. The orientation of the ribs + is defined in ribRotation. The number of ribs of the current rib + set is either defined by ribNumber or by spacing. + Three examples how ribs can be placed on the wing are + illustrated in the picture below. For more detailed information, + please refer to the description of each parameter. + + + + + + + + + + + + + + + + Defines the start of the rib defined in eta-xsi coordinates of a reference plane + + + + + + + Defines the start of the rib by a point on a reference curve, + such as a spar, but not an explicit sparPosition + + + + + + + Defines the location of the beginning of the rib using a specific sparPosition + + + + + + + + + Defines the end of the rib defined in eta-xsi coordinates of a reference plane + + + + + + + Defines the end of the rib defined by a point on a reference curve + such as a spar, but not an explicit sparPosition + + + + + + + Defines the location of the end of the rib using a specific sparPosition + + + + + + + + Defines the forward beginning of the ribs. It can either be a + sparUID or "trailingEdge" or "leadingEdge". + + + + + + + Defines the backward ending of the ribs. It can either be a + sparUID or "trailingEdge" or "leadingEdge". + + + + + + + + The spacing of the ribs defines the distance between two ribs, + measured on the + ribReferenceLine. First rib is placed at etaStart. + + + + + + + Defines the number of ribs in this ribSet. First rib is at + etaStart on the + referenceLine, last rib is at etaEnd. The spacing is constant on the + ribReferenceLine. + + + + + + + + The ribReference is the reference line for the computation of the rib set spacing. + It can either be a sparUID or "trailingEdge" or "leadingEdge" + + + + + + + + RibCrossingBehaviour can either be 'cross' or 'end'. If it is set to'end' the ribs + of this rib set will end at the intersection with another rib. + If it is set to + 'cross' the ribs of this rib set will continue at the intersection + with another rib. + + + + + + + + + + + + + + + + + + + + + + wingsAeroPerformanceType + + + wingsAeroPerformance type, containing + wingsAeroPerformance + + + + + + + + + + + + + + + + + + + Sections of the wing. + + + WingSections type, containing all the sections of the + wing. + + + + + + + + + + + + + + + + + + + Section of the wing. + + + + WingSection type, containing a wing section. The + sections contains elements, where the airfoils are defined. For + the definition of a wing at least two sections (root and tip) + have to be defined, but any number greater than 2 is also + possible. + Mathematically spoken a section is a coordinate system + that is translated, rotated and scaled relative to the wing + coordinate system. This transformation parameters are defined + within the transformation section. + In addition to the translation, which is defined in + the transformation part, the section can be translated by using + the positionings vectors (wing->positiongs). Translation of + the positionings vectors is added to the translation of the + section. + An example for wing sections can be found in the + picture below: + + + + + + + + + + + + + + Name of wing the wing section. + + + + + + Description of the wing section. + + + + + + + + + + + + + + + + + Segments of the wing. + + + WingSegments type, containing all the segments of the + wing. + + + + + + + + + + + + + + + + + + + Segment of the wing. + + + + A segment defines which two wing elements (=cross + sections) are linked to one wing segment. + An example for wing segments can be found in the + picture below: + + + + + + + + + + + + + + Name of wing the wing segment. + + + + + + Description of the wing segment. + + + + + + Reference to the element from which the + segment shall start. + + + + + Reference to the element at which the segment + shall end. + + + + + Optional and additional guidecurves to shape + the outer geometry. + + + + + + + + + + + + + + Shells of the wing + + + Within the wingShellType the upper and lower skin of a + and the skin stringers are defined. At 'skin' and 'stringer' the + skin and stringer properties of the complete componentSegment are + defined. If different skin or stringer properties should be + defined in a special region of the wing this can be done within + 'cells'. + If the stringer should not be defined explicitly, they + can be defined implizite by defining an equivalent material layer + and using a composite as material. + + + + + + + + + + + + + + + + + + + + + + Material properties of the wing skin. + + + + The wingSkinType describes the material properties of + the wing. + For composites materials: the positive z-direction is + from the outer side to the inner side. + For composites materials: the reference axis for the + orthotropyDirection is defined by the two leading edge points of + the 'from'- and the 'to'-element of the componentSegment + definition. The angle between the reference axis and the + orthotropyDirection equals the rotation around the z-reference + axis. For details, please refer to the picture below: + + + + + + + + + + + + + + + Material properties of the wing skin. + + + + + + + + + + + + + + Wing spars + + + + Spars type, a spar is defined by sparSegments that + stretch between multiple sparPositions. The spar definition is + very flexible in CPACS. Spars can start and end at any position + of the wing, spars can have kinks at any position of the wing + and spars can cross each other or merge. + At first the spar points (->sparPositions) have to + be defined. Spar points are defined using the relative + coordinates eta and xsi. Spar points do lay on wing middle + plane. + Two or more spar points are connected to on spar + segment (->sparSegments). Each spar segment can be seen as + one spar. The spar geometry between two spar points is defined + as a direct/straight connection in global coordinate system + and not in eta xsi coordinates of the component segment. + One spar point can be used by more than one spar, if + e.g. two spars are merging. The detailed cross section of the + spar is also defined with sparSegments. + Please find below a picture for an example definition + of 3 spars in one wing, by using spar position points and spar + segments: + + + + + + + + + + + + + + + + + + + + + + + + Definition of the wing stringers. + + + + Within the wingStringerType wing stringers are + defined. The stringer are defined by referencing on the + stringerStructureUID, where the shape and material settings of + one single stringer is defined. In addition the orientation and + the stringer pitch have to be defined: + One stringer intersects the point at the given xsi and + eta position. + + + + Alternatively, an explicit stringer definition can be + applied if the stringers shall be tapered. + + + + + + + + + + + + + This is the simple and default stringer + definition + + + + The pitch describes the distance between to + adjacent stringers in the plane rectangular to the stringer + elongation direction. + + + + + + Stringer angle: the reference axis for the + stringer angle is defined by the two leading edge points of + the 'from'- and the 'to'-element of the componentSegment + definition. The angle between the reference axis and the + stringers equals the rotation around the z-reference axis. For + details, please refer to the picture below. + + + + + + If the reference of the stringer angle shall + be different from the default implementation then this + parameter may be set. Allowed values include: leadingEdge, + trailingEdge and globalY. Furthermore, it is possible to + provide the UID of a spar. + + + + + + This is the explicit stringer definition. + Please note that for a consistent definition two out of the + possible three elements innerBorder (xsiLE, xsiTE), outerBorder + (xsiLE, xsiTE) and stringer angle (and angle reference) must be + defined. Any combination of two of the three is valid + + + + + The number of stringers; default is 0 + + + + + + Stringer angle: the reference axis for the + stringer angle is defined by the two leading edge points of + the 'from'- and the 'to'-element of the componentSegment + definition. The angle between the reference axis and the + stringers equals the rotation around the z-reference axis. For + details, please refer to the picture below. + + + + + + If the reference of the stringer angle shall + be different from the default implementation then this + parameter may be set. Allowed values include: leadingEdge, + trailingEdge and globalY. Furthermore, it is possible to + provide the UID of a spar. + + + + + Inner border xsi coordinate at the leading + edge of the stringer definition + + + + + Outer border xsi coordinate at the leading + edge of the stringer definition + + + + + Inner border xsi coordinate at the trailing + edge of the stringer definition + + + + + Outer border xsi coordinate at the trailing + edge of the stringer definition + + + + + + + + + + + + + + + wingStructuralMountsType + + + + + + + + + + + + + + + + + + + + + + Wings + + + Wings type, containing all the lifting surfaces (wings, + HTPs, VTPs, canards...) of an aircraft model. + + + + + + + + + + + + + + + + + + + Wing type, containing all a lifting surface (wing, HTP, + VTP, canard...) of an aircraft model. + + + + Wing type, containing all a lifting surface (wing, + HTP, VTP, canard...) of an aircraft model. + Position of the wing: The position of the wing is + defined using the transformation parameters. Using those + parameters, the wing coordinate system is translated, rotated + and scaled. + Definition of the wings outer shape: The outer shape + of the wing is defined by airfoils that are placed within the 3D + space. Two airfoils are combined to one wing segment within the + segments. For the definition of the positions of the airfoils, + different sections are defined. Within each section one or more + elements are defined. The airfoil shape is defined within the + elements. If the wings outer shape should e.g. have a step it is + possible to define two different airfoils in one section by + using two elements. In most cases each section will only include + one element. Positionings are vectors that are used for an + additional translation of the sections by using 'user friendly + paramaters' as e.g. sweep and dihedral. Please note, the first + positioning may be non-zero. Often it will be zero just to + locate the wing at the position stated by the translation, but + this is not necessary. Finally the wing segments are defined by + combining two consecutive elements. A more detailed description + is given within the different parameters. + Definition of control surfaces, wing structures, wing + fuel tank and wing fuselage attachment: those parts are defined + within componentSegments. Please refer to the documentation + there. + + + + + + + + + + + + + + Name of the wing. + + + + + Description of the wing. + + + + + UID of part to which the wing is mounted (if + any). The parent of the wing can e.g. be the fuselage. In each + aircraft model, there is exactly one part without a parent part + (The root of the connection hierarchy). + + + + + + + + + + + + + + + + + + + + The two elements that where the structural connection + is placed. + + + + + + + + + + + + + Element uID of the element of the CURRENT + componentSegment where the structural connection is placed. + + + + + + Element uID of the element of the second + componentSegment where the structural connection is placed. + + + + + + + + + + + + + + Two spars that are structurally connected. + + + + + + + + + + + + + Spar uID of the CURRENT componentSegment. + + + + + + Spar uID of the second componentSegment. + + + + + + + + + + + + + + wingWingAttachmentsSparsType + + + + + + + + + + + + + + + + + + + + + + List of wingWingAttachments. + + + + + + + + + + + + + + + + + + + + + + wingWingAttachmentType + + + Definition of the structural connection between two + wings resp. two componentSegments. Note: All structural + connections between two wings/componetSegments have to be defined + using wingWingAttachments. The wingWingAttachment has only be + defined in one of the two componentSegments, that are connected. + + + + + + + + + + + UID of the componentSegment, that is connected + with the current one. + + + + + + + Defines if the upper shell of the current + componentSegment is structurally connected to the upper or lower + shell of the second componentSegment. Can have the values + 'upperShell' or 'lowerShell'. + + + + + + + + + + + + + Defines if the lower shell of the current + componentSegment is structurally connected to the upper or lower + shell of the second componentSegment. Can have the values + 'upperShell' or 'lowerShell'. + + + + + + + + + + + + + + + + + + + + + xsiIsoLineType + + + Iso line described by point of same xsi coordinate. + Can be either segment or component segment coordinates. + + + + + + + + + + Relative spanwise position. Xsi refers to the segment or componentSegment depending on the referenced uID. + + + + + This reference uID determines the reference coordinate system. + If it points to a segment, then the eta value is considered to be in segment + eta coordinate; if it points to a componentSegment, + then componentSegment eta coordinate is used. + + + + + + + + + + + + + zCouplingsType + + + + + + + + + + + + + Definition of one z-coupling. + + + + + + + + + + + + + + zCouplingType + + + + + + + + + + + + + Reference to the control surface that is + connected to this control surface by the z-coupling.. + + + + + + Material of the movable part of the + z-coupling. + + + + + Definition of the attachment of the z-coupling + to this control surface. + + + + + Definition of the attachment of the z-coupling + to the other control surface. + + + + + + + + +