fix(a380x/flight model): Fix stall and auto rotate issues

.github/CHANGELOG.md

@@ -27,6 +27,7 @@
 1. [A380X/AP] Improved support of simulation rate 4x - @aguther (Andreas Guther)
 1. [A32NX/FANS] Restore Portuguese station codes - @tracernz (Mike)
 1. [A380X/MFD] Fixed DIRECT TO selection of active waypoint does nothing - @sognodelx (Sven Gross)
+1. [A380X/FLIGHT MODEL] Fix for stall and auto-rotation issues- @donstim (donbikes)
 
 ## 0.12.0
 

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 = 0, 0
+ThrustAnglesPitchHeading.0 = -15, 0
 Engine.1 = 15, -47.5, -4
-ThrustAnglesPitchHeading.1 = 0, 0
+ThrustAnglesPitchHeading.1 = -15, 0
 Engine.2 = 15, 47.5, -4
-ThrustAnglesPitchHeading.2 = 0, 0
+ThrustAnglesPitchHeading.2 = -15, 0
 Engine.3 = -10, 84, -1.5
-ThrustAnglesPitchHeading.3 = 0, 0
+ThrustAnglesPitchHeading.3 = -15, 0
 fuel_flow_scalar = 0; NOT
 
 [TURBINEENGINEDATA]

fbw-a380x/src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/flight_model.cfg

@@ -1,26 +1,6 @@
 ; 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
@@ -508,21 +488,21 @@ 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), should be 57.97 but increased to match reference MAC length
+wing_root_chord = 58.86 ; Wing root chord croot (FEET)
 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 = 6.5 ; Dihedral angle Lambda (DEGREES)
+wing_dihedral = 5.6 ; 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)
 wing_winglets_flag = 0 ; Has winglets true/false (MSFS doesn't use this parameter)
 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 = 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_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_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
@@ -533,15 +513,15 @@ 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; (is 23.43 horizontally, but 27.6 to 28.1 vertically)
+fuselage_diameter = 25; 
 fuselage_center_pos = 10, 0, 7.1
-elevator_area = 500 ; Elevator area (SQUARE FEET) OLD VALUE 593
+elevator_area = 1200 ; Elevator area (SQUARE FEET)
 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) 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
+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)
 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)
@@ -569,7 +549,7 @@ 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 = 0:1, 400:1
+elevator_trim_elasticity_table = 0:0.45, 50:0.7, 100:1.04, 115:1.5, 400:5.7
 ;controls_reactivity_scalar = 1 ; Reactivity scalar for all controls
 
 
@@ -578,7 +558,7 @@ 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 = 1.905 ; Change in lift due to flaps
+lift_coef_flaps = 1.5 ; 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
@@ -656,7 +636,7 @@ 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 = 0:1 ; scales control based on its deflection
+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
 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
@@ -665,6 +645,9 @@ 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]
 
@@ -676,7 +659,7 @@ parasite_drag_scalar = 1
 induced_drag_scalar = 1
 flap_induced_drag_scalar = 0.5
 elevator_effectiveness = 1
-elevator_maxangle_scalar = 0.7
+elevator_maxangle_scalar = 1
 aileron_effectiveness = 1
 rudder_effectiveness = 0.16
 rudder_maxangle_scalar = 1
@@ -794,11 +777,11 @@ 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 ; 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-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.1]
 type = 1 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
@@ -814,11 +797,11 @@ 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 ; 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-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.2]
 type = 2 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
@@ -834,8 +817,8 @@ 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 ; 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
+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