From b2a4f2fb50ab7237c1587d6cacd63990ce405dd1 Mon Sep 17 00:00:00 2001 From: Sascha Rudolf Date: Fri, 8 Nov 2024 12:40:21 +0100 Subject: [PATCH] Revert "fix(a380x/flight model): Fix stall and auto rotate issues (#9387)" This reverts commit b5bd6e639870548356a5fe502f7a9758efb3d869. --- .../AirPlanes/FlyByWire_A380_842/engines.cfg | 8 +- .../FlyByWire_A380_842/flight_model.cfg | 85 +++++++++++-------- 2 files changed, 55 insertions(+), 38 deletions(-) diff --git a/fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/engines.cfg b/fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/engines.cfg index a52204898c8..4448d42e8d2 100644 --- a/fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/engines.cfg +++ b/fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/engines.cfg @@ -18,13 +18,13 @@ master_ignition_switch = 0 starter_type = 2 ; 0=Electric, 1=Manual, 2=Bleed Air max_contrail_temperature = -39.724 Engine.0 = -10, -84, -1.5 -ThrustAnglesPitchHeading.0 = -15, 0 +ThrustAnglesPitchHeading.0 = 0, 0 Engine.1 = 15, -47.5, -4 -ThrustAnglesPitchHeading.1 = -15, 0 +ThrustAnglesPitchHeading.1 = 0, 0 Engine.2 = 15, 47.5, -4 -ThrustAnglesPitchHeading.2 = -15, 0 +ThrustAnglesPitchHeading.2 = 0, 0 Engine.3 = -10, 84, -1.5 -ThrustAnglesPitchHeading.3 = -15, 0 +ThrustAnglesPitchHeading.3 = 0, 0 fuel_flow_scalar = 0; NOT [TURBINEENGINEDATA] diff --git a/fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/flight_model.cfg b/fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/flight_model.cfg index 14853ff78ba..be3f520f2f5 100644 --- a/fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/flight_model.cfg +++ b/fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/flight_model.cfg @@ -1,6 +1,26 @@ ; Copyright (c) 2023-2024 FlyByWire Simulations ; SPDX-License-Identifier: GPL-3.0 +; A380 MSN 225 - WV03 A380-842 +; 07 Mar 2023 - Fuel System Update + +; 10 Feb 2024 - Masses (tanks/cargo) shift 5m fwd to match visual model +; Contact point of wing gear slightgly set higher so it gets less plane weight (shift weight on nose) +; Main gears contact points pushed a bit aft as a compromise between correct tilt animation and weight distribution + +; 14 Feb 2024 - Moved CG while keeping correct %Mac offset by moving aero center forward +; Changed contact points and empty mass to match real MSN empty weight load sheet + +; 15 Feb 2024 - Activate new spring method and update strut springs + +; 19 Jul 2024 - Adjust CG, wheels and fuel tanks to correct model origin to Airbus reference datum offset +; The position of the nose in the model coord. system is 35.1927m. The Airbus reference datum distance from the nose is 7.33m. +; So, the conversion from HArm value to model coordinates in m is: model_coord = (35.1927m + 7.33m) - harm_value + +; 13 Sept 2024 fixed some invalid entries in the trigger section + +; 22 Oct 2024 Fixed numerous issues with the fuel system. Code added to address MSFS fuel system issues and restrict transfers until airplane is in flight. + [VERSION] major = 1 minor = 0 @@ -488,10 +508,10 @@ Trigger.42 = Name:CGControlTransferEnd#Condition:Manual#EffectTrue:CloseValve.Tr [AIRPLANE_GEOMETRY] wing_area = 9096.0 ; Wing area S (SQUARE FEET) wing_span = 261.65 ; Wing span b (FEET) -wing_root_chord = 58.86 ; Wing root chord croot (FEET) +wing_root_chord = 58.86 ; Wing root chord croot (FEET), should be 57.97 but increased to match reference MAC length wing_camber = 1 ; (DEGREES) (Unkown - estimated value) wing_thickness_ratio = 0.05 ; Local thickness is local_chord(x)*wing_thickness_ratio, x = lateral coord -wing_dihedral = 5.6 ; Dihedral angle Lambda (DEGREES) +wing_dihedral = 6.5 ; Dihedral angle Lambda (DEGREES) wing_incidence = 2 ; Wing incidence (DEGREES) (unknown) wing_twist = -5.5 ; Wing twist epsilon (DEGREES) oswald_efficiency_factor = 0.70 ; Wing Oswald efficiency factor e (non dimensional) @@ -499,10 +519,10 @@ wing_winglets_flag = 0 ; Has winglets true/false (MSFS doesn't use this paramete wing_sweep = 37 ; Wing sweep (DEGREES) ;wing_pos_apex_lon = 0 ; Longitudinal (z) position of wing apex w.r.t reference datum (FEET) (not used) wing_pos_apex_vert = -2 ; Vertical (y) position of wing apex w.r.t reference datum (FEET) (estimated from mesh drawing) -htail_area = 1603 ; Horizontal tail area (SQUARE FEET) -htail_span = 80 ; Horizontal tail span (FEET) -htail_pos_lon = -105 ; Longitudinal (z) position of horizontal tail w.r.t reference datum (FEET) -htail_pos_vert = 13.8 ; Vertical (y) position of horizontal tail w.r.t reference datum (FEET) +htail_area = 1250 ; Horizontal tail area (SQUARE FEET) -original 1603 +htail_span = 80 ; Horizontal tail span (FEET) -OLD VALUE 83.50 +htail_pos_lon = -105 ; Longitudinal (z) position of horizontal tail w.r.t reference datum (FEET) -76.6 +htail_pos_vert = 13.8 ; Vertical (y) position of horizontal tail w.r.t reference datum (FEET) 13.8 11.35 -OLD VALUE 14.8 htail_incidence = -2 ; Horizontal tail incidence (DEGREES) OLD VALUE 0 htail_sweep = 38 ; Horizontal tail sweep angle (DEGREES) htail_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*htail_thickness_ratio, x = lateral coord @@ -513,15 +533,15 @@ vtail_pos_lon = -90.5 ; Longitudinal (z) position of vertical tail w.r.t refere vtail_pos_vert = 37 ; Vertical (y) position of vertical tail w.r.t reference datum (FEET) vtail_thickness_ratio = 0.02 ; Local thickness is local_chord(x)*vtail_thickness_ratio, x = lateral coord fuselage_length = 230.97 ; Nose to tail (FEET) -fuselage_diameter = 25; +fuselage_diameter = 25; (is 23.43 horizontally, but 27.6 to 28.1 vertically) fuselage_center_pos = 10, 0, 7.1 -elevator_area = 1200 ; Elevator area (SQUARE FEET) +elevator_area = 500 ; Elevator area (SQUARE FEET) OLD VALUE 593 aileron_area = 258 ; Elevator area (SQUARE FEET) rudder_area = 416.6 ; Elevator area (SQUARE FEET) -elevator_up_limit = 30 ; Elevator max deflection up angle (DEGREES) -elevator_down_limit = 20 ; Elevator max deflection down angle (absolute value) (DEGREES) -aileron_up_limit = 30; Aileron max deflection angle (DEGREES) -aileron_down_limit = 20; Aileron max deflection down angle (absolute value) (DEGREES) +elevator_up_limit = 30 ; Elevator max deflection up angle (DEGREES) Real value is 30 +elevator_down_limit = 20 ; Elevator max deflection down angle (absolute value) (DEGREES) Real value is 17 +aileron_up_limit = 30; Aileron max deflection angle (DEGREES) Real value is 25 +aileron_down_limit = 20; Aileron max deflection down angle (absolute value) (DEGREES) Real value is 25 rudder_limit = 30; Rudder max deflection angle (absolute value) (DEGREES) rudder_trim_limit = 25.5 ; Rudder trim max deflection angle (absolute value) (DEGREES) elevator_trim_up_limit = 10 ; Elevator trim max angle (absolute value) (DEGREES) @@ -549,7 +569,7 @@ fly_by_wire = 0 ; Fly-by-wire available true/false elevator_elasticity_table = 0:1, 400:1 aileron_elasticity_table = 0:1, 400:1 rudder_elasticity_table = 0:1, 400:1 -elevator_trim_elasticity_table = 0:0.45, 50:0.7, 100:1.04, 115:1.5, 400:5.7 +elevator_trim_elasticity_table = 0:1, 400:1 ;controls_reactivity_scalar = 1 ; Reactivity scalar for all controls @@ -558,7 +578,7 @@ lift_coef_pitch_rate = -47.338 ; The change in lift per change in pitch rate lift_coef_daoa = 0 ; lift per change in angle of attack rate lift_coef_delta_elevator = -1.143 ; The change in lift per change in elevator deflection lift_coef_horizontal_incidence = 0 ; The change in lift per change in horizontal incidence angle -lift_coef_flaps = 1.5 ; Change in lift due to flaps +lift_coef_flaps = 1.905 ; Change in lift due to flaps lift_coef_spoilers = -0.546875 ; Change in lift due to spoilers drag_coef_zero_lift = 0.015 ; The zero lift drag polar drag_coef_flaps = 0.0706 @@ -636,7 +656,7 @@ yaw_moment_delta_rudder_mach_table = 0:0 yaw_moment_delta_aileron_mach_table = 0:0 yaw_moment_yaw_rate_mach_table = 0:0 yaw_moment_roll_rate_mach_table = 0:0 -elevator_scaling_table = -0.35:3.0, -0.3:2.5, -0.26:1.5, -0.1:1, 0:1, 0.55:1 ; scales control based on its deflection +elevator_scaling_table = 0:1 ; scales control based on its deflection aileron_scaling_table = 0:1 ; scales control based on its deflection rudder_scaling_table = 0:1 ; scales control based on its deflection aileron_load_factor_effectiveness_table = 0:1 ; scaling of roll_moment_delta_aileron versus gravity forces, G effects on aileron effectiveness, acts on roll_moment_delta_aileron @@ -645,9 +665,6 @@ lift_coef_at_drag_zero_flaps = 0.40000 ;elevator_lift_coef = 0.5 ; Defines elevator lift vs elevator angle-of-attack ;rudder_lift_coef = 0.5 ; Defines rudder lift vs rudder angle-of-attack ;fuselage_lateral_cx = 0.5; Defines fuselage lift and side force vs fuselage angle-of-attack and beta -StallDef_StartRatio = 1 -StallDef_EndRatio = 2 -StallDef_airflowdetachspeed = 0.1 [FLIGHT_TUNING] @@ -659,7 +676,7 @@ parasite_drag_scalar = 1 induced_drag_scalar = 1 flap_induced_drag_scalar = 0.5 elevator_effectiveness = 1 -elevator_maxangle_scalar = 1 +elevator_maxangle_scalar = 0.7 aileron_effectiveness = 1 rudder_effectiveness = 0.16 rudder_maxangle_scalar = 1 @@ -777,11 +794,11 @@ drag_scalar = 0 ; Scalar coefficient to ponderate global flap drag coef (non dim pitch_scalar = 0 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned) max_on_ground_position = 5 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found. flaps-position.0 = 0.00, -1, 0.00, 0.00 ; CONF 0 -flaps-position.1 = 0.01, -1, 1.00, 1.00, 1.00, 0.00 0.00 ; CONF 1 -flaps-position.2 = 8.00, 222, 1.00, 1.00, 1.00, 0.00 0.00 ; CONF 1+F -flaps-position.3 = 17.00, 220, 1.00, 1.00 1.00, 0.00 0.00 ; CONF 2 -flaps-position.4 = 26.00, 196, 1.00, 1.00 1.00, 0.00 0.00 ; CONF 3 -flaps-position.5 = 32.00, 182, 1.00, 1.00 1.00, 0.00 -0.40 ; CONF FULL +flaps-position.1 = 0.01, -1, 1.00, 1.00 ; CONF 1 +flaps-position.2 = 8.00, 222, 1.00, 1.00 ; CONF 1+F +flaps-position.3 = 17.00, 220, 1.00, 1.00 ; CONF 2 +flaps-position.4 = 26.00, 196, 1.00, 1.00 ; CONF 3 +flaps-position.5 = 32.00, 182, 1.00, 1.00 ; CONF FULL [FLAPS.1] type = 1 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge @@ -797,11 +814,11 @@ drag_scalar = 1 ; Scalar coefficient to ponderate global flap drag coef (non dim pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned) max_on_ground_position = 5 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found. flaps-position.0 = 0.00, -1, 0, 0.0 ; CONF 0 -flaps-position.1 = 5.0, -1, 1.00, 1.00 1.00, 0.00 0.00 ; CONF 1 -flaps-position.2 = 10.00, 222, 0.70, 0.95, 1.00, 0.00 0.00 ; CONF 1+F -flaps-position.3 = 15.00, 220, 1.30, 1.15, 1.00, 0.00 0.00 ; CONF 2 -flaps-position.4 = 20.00, 196, 1.50, 1.00, 1.00, 0.00 0.00 ; CONF 3 -flaps-position.5 = 32.00, 182, 1.00, 1.02 1.00, 0.00 -0.40 ; CONF FULL +flaps-position.1 = 5.0, -1, 1.00, 1.00 ; CONF 1 +flaps-position.2 = 10.00, 222, 0.70, 1.30 ; CONF 1+F +flaps-position.3 = 15.00, 220, 1.30, 1.25 ; CONF 2 +flaps-position.4 = 20.00, 196, 1.50, 1.50 ; CONF 3 +flaps-position.5 = 32.00, 182, 1.00, 1.00 ; CONF FULL [FLAPS.2] type = 2 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge @@ -817,8 +834,8 @@ drag_scalar = 0.5 ; Scalar coefficient to ponderate global flap drag coef (non d pitch_scalar = 1 ; Scalar coefficient to ponderate global flap pitch coef (non dimensioned) max_on_ground_position = 5 ; Dynamically set in-tool to last flap-position index by defaut when -1 is found. flaps-position.0 = 0.00, -1, 1.00, 1.00 ; CONF 0 -flaps-position.1 = 20.00, 263, 1.85, 0.55, 1.00, 0.00 0.00 ; CONF 1 -flaps-position.2 = 20.01, 222, 0.70, 0.99, 1.00, 0.00 0.00 ; CONF 1+F -flaps-position.3 = 20.02, 220, 1.30, 1.00, 1.00, 0.00 0.00 ; CONF 2 -flaps-position.4 = 23.00, 196, 1.50, 1.00, 1.00, 0.00 0.00 ; CONF 3 -flaps-position.5 = 23.01, 182, 1.00, 1.00, 1.00, 0.00 -0.40 ; CONF FULL +flaps-position.1 = 20.00, 263, 1.85, 0.55 ; CONF 1 +flaps-position.2 = 20.01, 222, 0.70, 1.00 ; CONF 1+F +flaps-position.3 = 20.02, 220, 1.30, 1.25 ; CONF 2 +flaps-position.4 = 23.00, 196, 1.50, 1.50 ; CONF 3 +flaps-position.5 = 23.01, 182, 1.00, 1.00 ; CONF FULL