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fix(a380x/flight model): Fix stall and auto rotate issues (#9387)
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* Update CHANGELOG.md

* Update engines.cfg

* Update flight_model.cfg

* Update flight_model.cfg

* Update flight_model.cfg

* Update CHANGELOG.md

* Update flight_model.cfg

* fix: re-added lost changelog entry

* Update engines.cfg

* Update flight_model.cfg

* Update flight_model.cfg

---------

Co-authored-by: alepouna <[email protected]>
Co-authored-by: 2hwk <[email protected]>
Co-authored-by: Saschl <[email protected]>
Co-authored-by: Michael Corcoran <[email protected]>
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@donstim @alepouna
@2hwk @Saschl @tracernz
5 people committed Nov 7, 2024
1 parent 6b17093 commit b5bd6e6
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12 changes: 12 additions & 0 deletions .github/CHANGELOG.md
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Expand Up @@ -21,6 +21,18 @@
1. [A380X/FMS] Fixed layouting issue on FMS/ACTIVE/PERF/T.O page for some users - @flogross89 (floridude)
1. [A380X/TELEX] Added popup for telex consent @saschl (saschl) @Maximilian-Reuter (\_chaoz)
1. [A32NX/CAMERA] Improved default camera position for Virtual Reality (VR) - @aguther (Andreas Guther)
1. [A380X/TELEX] Added popup for telex consent - @saschl (saschl) @Maximilian-Reuter (\_chaoz)
1. [ND] Fix memory leak when using TERR ON ND - @Nufflee (nufflee)
1. [A380X/OVHD] Fix RCDR GND CTL button/logic - @flogross89 (floridude)
1. [A380X] Various fixes in FMS and ECL - @flogross89 (floridude)
1. [A380X/EWD] QoL: Add soft keys to EWD checklists, can be enabled via EFB - @flogross89 (floridude)
1. [A380X/LIGHTS] Implemented LOGO LT switch funcionality - @ImenesFBW (Imenes)
1. [A380X/SD] Added correct ECP ALL button SD page cycling to the A380X - @frankkopp (Frank Kopp)
1. [A380/MFD] Limit keyboard inputs to keys present in the KCCU and remap comma to decimal dot - @beheh (Benedict Etzel)
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

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8 changes: 4 additions & 4 deletions .../src/base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/engines.cfg
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Expand Up @@ -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]
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85 changes: 34 additions & 51 deletions ...base/flybywire-aircraft-a380-842/SimObjects/AirPlanes/FlyByWire_A380_842/flight_model.cfg
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@@ -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
Expand Down Expand Up @@ -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
Expand All @@ -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)
Expand Down Expand Up @@ -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


Expand All @@ -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
Expand Down Expand Up @@ -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
Expand All @@ -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]

Expand All @@ -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
Expand Down Expand Up @@ -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
Expand All @@ -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
Expand All @@ -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

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