fix(A380x/fight model): Improve pitch response sensitivity

.github/CHANGELOG.md

@@ -99,6 +99,7 @@
 1. [A32NX/EFB] Added Departure Change Checklist to EFB - @FlyByTim (FlyByTim)
 1. [A380X/MFD] Fix CPNY F-PLN REQUEST button disabled when airport ICAO not found in failed Simbrief import - @heclak (Heclak)
 1. [A380X/RMP] Fix FO RMP integrated lights not working - @heclak (Heclak)
+1. [A380X/FLIGHT MODEL] Improve pitch response  - @donstim (donbikes)
 
 ## 0.14.0
 

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

@@ -19,7 +19,7 @@ reference_datum_position = 0, 0, 0 ; Position of reference datum relative to FS(
 empty_weight_CG_position = 18, 0, 2.8 ; Position of airplane empty weight CG relative to reference datum (FEET), z, x, y
 CG_forward_limit = 0.10 ; Gravity center forward limit (longitudinal offset) for longitudinal stability (this value used just to prevent beyond cg limit messages)
 CG_aft_limit = 0.44 ; Gravity center after limit (longitudinal offset z) w.r.t reference datum for longitudinal stability (FEET)
-empty_weight_pitch_MOI = 38245361 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
+empty_weight_pitch_MOI = 40345361 ; Empty pitch moment of inertia, Jxx (SLUG SQ FEET)
 empty_weight_roll_MOI = 53559900 ; Empty roll moment of inertia, Jzz (SLUG SQ FEET)
 empty_weight_yaw_MOI = 88229309 ; Empty yaw moment of inertia, Jyy (SLUG SQ FEET)
 empty_weight_coupled_MOI = 1000 ; Empty transverse moment of inertia, Jyz (SLUG SQ FEET)
@@ -572,7 +572,7 @@ Trigger.46 = Name:OuterTankRightEmpty#Condition:Manual#EffectTrue:StopPump.Right
 ;
 ; Feed tanks 2 and 3 forward transfer valves 1_2 and their corresponding lines are no longer used.
 ;
-; Load alleviation transfer are not currently simulated.
+; Load alleviation transfers are not currently simulated.
 
 [AIRPLANE_GEOMETRY]
 wing_area = 9096.0 ; Wing area S (SQUARE FEET)
@@ -641,29 +641,28 @@ rudder_elasticity_table = 0:1, 400:1
 elevator_trim_elasticity_table = 0:0.40, 40:0.74, 80:0.95, 100:1.0, 400:1.5
 
 [AERODYNAMICS]
-lift_coef_flaps = 1.300 ; Change in lift due to flaps
+lift_coef_flaps = 1.326 ; Change in lift due to flaps
 lift_coef_spoilers = -0.546875 ; Change in lift due to spoilers
 drag_coef_zero_lift = 0.02016 ; The zero lift drag polar
-drag_coef_flaps = 0.278 ; Change in drag due to flaps
+drag_coef_flaps = 0.285 ; Change in drag due to flaps
 drag_coef_gear = 0.019 ; Change in drag due to landing gear
 drag_coef_spoilers = 0.025;  ; Change in drag due to spoilers
 compute_aero_center = 0
 aero_center_lift = 11 ; Init to center
 lift_coef_aoa_table = -3.15:0, 0:0.095, 0.139:0.95, 0.2:1.24, 0.314:1.60, 0.36:1.70, 0.5:1.58, 3.15:0
-lift_coef_ground_effect_mach_table = 0:0.71, 0.1:0.69, 0.2:0.68, 0.3:0.67, 0.4:0.66, 0.5:0.64, 1.0:0.60
+lift_coef_ground_effect_mach_table = 0:1.02, 0.1:1.01, 0.2:1.005, 0.3:1.00, 0.4:0.99, 0.5:0.97, 1.0:0.94
 drag_coef_zero_lift_mach_tab = 0:0, 0.5:0, 0.55:0, 0.6:0.00012, 0.65:0.00026, 0.7:0.0004, 0.75:0.00061, 0.8:0.0010, 0.85:0.0018, 0.9:0.0031, 0.95:0.005, 1.0:0.0082
 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
 lift_coef_at_drag_zero = 0.12500
 lift_coef_at_drag_zero_flaps = 0.40000
 fuselage_lateral_cx = 0.5; Defines fuselage lift and side force vs fuselage angle-of-attack and beta
-StallDef_StartRatio = 1.6  ; will need to be adjusted for proper stall when direct law is implemented
-StallDef_EndRatio = 2  ; will need to be adjusted for proper stall when direct law is implemented
+StallDef_StartRatio = 2.0  ; will need to be adjusted for proper stall when direct law is implemented
+StallDef_EndRatio = 3.0  ; will need to be adjusted for proper stall when direct law is implemented
 ;StallDef_airflowdetachspeed = 0.01
-Stall_AileronAddIncidence = 7  ; will need to be adjusted for proper stall when direct law is implemented
-Stall_TipAddIncidence = 7  ; will need to be adjusted for proper stall when direct law is implemented
+Stall_AileronAddIncidence = 0  ; will need to be adjusted for proper stall when direct law is implemented
+Stall_TipAddIncidence = 0  ; will need to be adjusted for proper stall when direct law is implemented
 
 ;Legacy Aerodynamics Parameters (not used by modern flight model, but must be present)
 
@@ -749,15 +748,15 @@ cruise_lift_scalar = 1
 parasite_drag_scalar = 1
 induced_drag_scalar = 0.853
 flap_induced_drag_scalar = 0.35
-elevator_effectiveness = 1.3
-elevator_maxangle_scalar = 1
+elevator_effectiveness = 0.97
+elevator_maxangle_scalar = 0.85
 aileron_effectiveness = 1
 rudder_effectiveness = 0.2
 rudder_maxangle_scalar = 1
-pitch_stability = 4
+pitch_stability = 4.5
 roll_stability = 1
 yaw_stability = 1
-pitch_gyro_stability = 6
+pitch_gyro_stability = 4.5
 roll_gyro_stability = 4.5
 yaw_gyro_stability = 1
 elevator_trim_effectiveness = 1.05
@@ -892,10 +891,10 @@ max_on_ground_position = 5 ; Dynamically set in-tool to last flap-position index
 ;Flap section index number, flap position in degrees, airspeed limit, drag scalar, lift scalar, area scalar, add camber (radians), add aft feet (pos value moves center of lift forward), add incidence - scalar setting proportion of additional lift added at 0 degrees AOA (with 100% at stall AOA)
 flaps-position.0 =  0.00,  -1, 0.00,  0.00,  1.00, 0.00,  0.00, 1.00 ; CONF 0
 flaps-position.1 =  5.00,  -1, 0.05,  0.01,  1.00, 0.00,  0.00, 1.00 ; CONF 1
-flaps-position.2 = 10.00, 222, 0.69,  0.26,  1.00, 0.00,  2.00, 1.00 ; CONF 1+F
-flaps-position.3 = 15.00, 220, 0.76,  0.41, 1.00, 0.005,  3.00, 1.00 ; CONF 2
-flaps-position.4 = 20.00, 196, 1.41,  1.28,  1.02, 0.01,  3.50, 1.00 ; CONF 3
-flaps-position.5 = 32.00, 182, 0.98, 0.997,  1.03, 0.015, 4.00, 1.00 ; CONF FULL
+flaps-position.2 = 10.00, 222, 0.69,  0.275, 1.00, 0.00,  2.00, 1.00 ; CONF 1+F
+flaps-position.3 = 15.00, 220, 0.76,  0.42,  1.00, 0.005, 3.00, 1.00 ; CONF 2
+flaps-position.4 = 20.00, 196, 1.41,  1.279, 1.02, 0.01,  3.50, 1.00 ; CONF 3
+flaps-position.5 = 32.00, 182, 0.98,  0.997, 1.03, 0.015, 4.00, 1.00 ; CONF FULL
 
 [FLAPS.2]
 type = 2 ; Flap type 0 = None, 1 = trailing edge, 2 = leading edge
@@ -910,9 +909,9 @@ 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.
 ;Flap section index number, flap position in degrees, airspeed limit, drag scalar, lift scalar, area scalar, add camber (radians), add aft feet (pos value moves center of lift forward), add incidence - scalar setting proportion of additional lift added at 0 degrees AOA (with 100% at stall AOA)
-flaps-position.0 =  0.00,  -1, 1.00, 1.00,   1.00, 0.00,  0.00, 0.00 ; CONF 0
-flaps-position.1 = 20.00, 263, 0.10, 0.10,   1.00, 0.006, 0.00, 0.00 ; CONF 1
-flaps-position.2 = 20.01, 222, 0.70, 0.26,   1.00, 0.006, 0.00, 0.00 ; CONF 1+F
-flaps-position.3 = 20.02, 220, 0.76, 0.41,   1.00, 0.006, 0.00, 0.00 ; CONF 2
-flaps-position.4 = 23.00, 196, 1.44, 1.2835, 1.00, 0.01,  0.00, 0.00 ; CONF 3
-flaps-position.5 = 23.01, 182, 1.00, 1.00,   1.00, 0.01,  0.00, 0.00 ; CONF FULL
+flaps-position.0 =  0.00,  -1, 1.00,  1.00,  1.00, 0.00,  0.00, 0.00 ; CONF 0
+flaps-position.1 = 20.00, 263, 0.10,  0.10,  1.00, 0.006, 0.00, 0.00 ; CONF 1
+flaps-position.2 = 20.01, 222, 0.70,  0.26,  1.00, 0.006, 0.00, 0.00 ; CONF 1+F
+flaps-position.3 = 20.02, 220, 0.76,  0.42,  1.00, 0.006, 0.00, 0.00 ; CONF 2
+flaps-position.4 = 23.00, 196, 1.405, 1.274, 1.00, 0.01,  0.00, 0.00 ; CONF 3
+flaps-position.5 = 23.01, 182, 1.00,  1.00,  1.00, 0.01,  0.00, 0.00 ; CONF FULL