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Copy pathA-29B.lua
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A-29B.lua
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--mounting 3d model paths and texture paths
mount_vfs_model_path (current_mod_path.."/Shapes")
mount_vfs_texture_path (current_mod_path.."/Cockpit/Textures/")
mount_vfs_model_path (current_mod_path.."/Cockpit/Shape")
mount_vfs_liveries_path (current_mod_path.."/Liveries")
mount_vfs_texture_path (current_mod_path.."/Textures/A-29B.zip")
mount_vfs_texture_path (current_mod_path.."/Textures/")
mount_vfs_sound_path (current_mod_path.."/Sounds")
spinner_tip_position = {3.594, -0.552, 0}
empty_cg_position = (spinner_tip_position[1] - 3.454) - 1.820 * 0.335
A_29B = {
Name = 'A-29B',
DisplayName = _('A-29B'),
Cannon = "yes",
HumanCockpit = false,
HumanCockpitPath = current_mod_path..'/Cockpit/',
Picture = "A-29B.png",
Rate = 40, -- RewardPoint in Multiplayer
Shape = "A-29B",
propellorShapeType = "3ARG_PROC_BLUR",
propellorShapeName = 'a29b_blade.fbx',
debrisGeneration = true,
shape_table_data =
{
{
file = 'A-29B';
life = 20; -- lifebar
vis = 3; -- visibility gain.
desrt = 'Fighter-2-crush'; -- Name of destroyed object file name
fire = { 300, 2}; -- Fire on the ground after destoyed: 300sec 2m
username = 'A-29B';
index = WSTYPE_PLACEHOLDER;---------------------------------------------------------------------------------------
classname = "lLandPlane";
positioning = "BYNORMAL";
},
-- no need for this as we are using a built in destroyed model
-- {
-- name = "A-29B-collision";
-- file = "A-29B-collision";
-- fire = { 240, 2};
-- },
},
-------------------------
-- add model draw args for network transmitting to this draw_args table (32 limit)
net_animation ={
0, -- front gear
-- 1, -- front gear suspension
2, -- nose wheel steering
3, -- main gear
-- 4, -- main gear suspension
5, -- main gear
-- 6, -- main gear suspension
9, -- right flap
10, -- left flap
11, -- right aileron
12, -- left aileron
15, -- right elevator
16, -- left elevator
17, -- rudder
21, -- speadbreak
38, -- canopy
-- 39, -- pilots heads
-- 49, -- nav lights
50, -- pilots fron eject
-- 51, -- landing lights
-- 77, -- wheel rollAngle
83, -- formation lights
-- 99, -- front pilot up down
101, -- wheel rolling
102, -- wheel rolling
103, -- wheel rolling
-- 114, -- canopy
190, -- nav light
191, -- nav light
192, -- strobe light
193, -- landing light
-- 198, -- beacon light
200, -- beacon light
201, -- beacon rotation
208, -- taxi light
209, -- search light
308, -- pylons
309, -- pylons
310, -- pylons
311, -- pylons
312, -- pylons
-- 337, -- back pilot head left right
-- 399, -- back pilot head up down
407, -- propellerer
472, -- back pilot disapear
},
mapclasskey = "P0091000024",
--WorldID = 54,
--index = A_29B;
--attribute = {wsType_Air, wsType_Airplane, wsType_Fighter, A_29B, Su_25T, "Fighters", "Refuelable",},
--Categories= {"{78EFB7A2-FD52-4b57-A6A6-3BF0E1D6555F}", "Interceptor",},
index = WSTYPE_PLACEHOLDER;
attribute = {wsType_Air, wsType_Airplane, wsType_Fighter, WSTYPE_PLACEHOLDER , "Fighters", "Refuelable",},
Categories = {"{78EFB7A2-FD52-4b57-A6A6-3BF0E1D6555F}", "Interceptor",},
M_empty = 3356, -- kg
M_nominal = 3900, -- kg -- kg ~ %50 fuel, combat load
M_max = 5400, -- kg
M_fuel_max = 495, -- utilizável 495 --509 + 239 + 249*2 + 231, -- kg Asas, Fuselage, Subalar, Ventral,
M_fuel_per_tank = {245, 250}, -- kg
H_max = 10668 , -- m
average_fuel_consumption = 0.302, -- this is highly relative, but good estimates are 36-40l/min = 28-31kg/min = 0.47-0.52kg/s -- 45l/min = 35kg/min = 0.583kg/s
defFuelRatio = 0.68, -- default fuel in shares from complete
CAS_min = 53, -- if this is not OVERAL FLIGHT TIME, but jus LOITER TIME, than it sholud be 10-15 minutes.....CAS capability in minute (for AI)
V_opt = 240/1.944,-- Cruise speed (for AI) –- Assume Mach 0.80 at 20000 ft as optimal. See -- http://www.nasa.gov/centers/dryden/pdf/87789main_H-636.pdf and –- http://www.hochwarth.com/misc/AviationCalculator.html –- Mach 0.8 at 20000 = XXX kts TAS = XXX m / s
V_take_off = 120/1.944, -- Take off speed in m/s (for AI)
V_land = 125/1.944, -- Land speed in m/s (for AI)
V_max_sea_level = 320/1.944, -- Max speed at sea level in m/s (for AI)
V_max_h = 210/1.944, -- Max speed at max altitude in m/s (for AI)
Vy_max = 12, -- Max climb speed in m/s (for AI)
Mach_max = 0.562, -- Max speed in Mach (for AI)
Ny_min = -4, -- Min G (for AI)
Ny_max = 8.0, -- Max G (for AI)
Ny_max_e = 8.0, -- Max G (for AI)
AOA_take_off = math.rad(9.0), -- AoA in take off (for AI) -- in radians
bank_angle_max = 60, -- Max bank angle (for AI)
has_afteburner = false, -- AFB yes/no
has_speedbrake = true, -- Speedbrake yes/no
has_differential_stabilizer = false, -- differential stabilizers
main_gear_pos = {-0.66, -2.13, 1.813}, --{-1, -2.03, 2.},
nose_gear_pos = {2.544, -2.184, 0}, --{2.808, -2.09, 0},
wheel_steering_angle_max = math.rad(20), -- radians
tand_gear_max = 0.363970234, -- tangent of degrees of rotation max of nose wheel steering
nose_gear_amortizer_direct_stroke = 0.00, -- down from nose_gear_pos !!!
nose_gear_amortizer_reversal_stroke = -0.156, -- up
nose_gear_amortizer_normal_weight_stroke = -0.056,
main_gear_amortizer_direct_stroke = 0.00, -- down from main_gear_pos !!!
main_gear_amortizer_reversal_stroke = -0.156, -- up
main_gear_amortizer_normal_weight_stroke = -0.056,
nose_gear_wheel_diameter = 0.433, --in m
main_gear_wheel_diameter = 0.563, -- in m
wing_area = 19.4, -- wing area in m2
wing_span = 11.135, -- wing span in m
wing_chord = 1.82,
wing_type = 0, -- 0 = Fixed wing, 1 = Variable geometry, 2 = Fold-able wing
thrust_sum_max = 17000, -- thrust in kg (44kN)
thrust_sum_ab = 17000, -- thrust inkg (71kN)
length = 11.332, -- full lenght in m
height = 3.974, -- height in m
flaps_maneuver = 1.0, -- Max flaps in take-off and maneuver (0.5 = 1st stage; 1.0 = 2nd stage) (for AI)
range = 1568, -- Max range in km (for AI)
RCS = 2.5, -- Radar Cross Section m2
IR_emission_coeff = 0.1, -- Normal engine -- IR_emission_coeff = 1 is Su-27 without afterburner. It is reference.
IR_emission_coeff_ab = 0.1, -- With afterburner
wing_tip_pos = {-0.39, -0.412, 5.591}, -- wingtip coords for visual effects
brakeshute_name = 0, -- Landing - brake chute visual shape after separation
flaps_transmission = "Electrical",
undercarriage_transmission = "Hydraulic",
-- The following is used for graphical AB effects
engines_count = 1, -- Engines count
engines_nozzles =
{
[1] =
{
pos = {2.427,-0.565,0.563}, -- nozzle coords
elevation = 0, -- AFB cone elevation –- for engines mounted at an angle to fuselage, change elevation
diameter = 0*0.1, -- AFB cone diameter
exhaust_length_ab = -3.0, -- lenght in m
exhaust_length_ab_K = 0.3, -- AB animation
engine_number = 1, --both to first engine
smokiness_level = 0.1, --both to first engine
},
[2] =
{
pos = {2.427,-0.565,-0.563}, -- nozzle coords
elevation = 0, -- AFB cone elevation
diameter = 0*0.1, -- AFB cone diameter
exhaust_length_ab = -3.0, -- lenght in m
exhaust_length_ab_K = 0.3, -- AB animation
engine_number = 1, --both to first engine
smokiness_level = 0.1, --both to first engine
},
}, -- end of engines_nozzles
crew_size = 2,
crew_members =
{
[1] =
{ pilot_name = "pilot_f86",
ejection_seat_name = 17,
drop_canopy_name = 'A-29B CANOPY',
pos = {0, 0.3, 0}, -- location of your pilot ejecting,
can_be_playable = true,
role = "pilot",
role_display_name = _("Pilot"),
ejection_order = 0,
}, -- end of [1]
[2] =
{ pilot_name = "pilot_f86",
ejection_seat_name = 17,
drop_canopy_name = 0,
pos = {-1.4, 0.5, 0},
pilot_body_arg = 472,
can_be_playable = false,
role = "instructor",
role_display_name = _("Instructor pilot"),
ejection_order = 1,
}, -- end of [2]
}, -- end of crew_members
fires_pos =
{
[1] = {-2.117, -0.9, 0},
[2] = {0.500, 0.213, 0},
[3] = {0.500, 0.213, -2.182},
[4] = {-0.82, 0.265, 2.774},
[5] = {-0.82, 0.265, -2.774},
[6] = {-0.82, 0.255, 2.7274},
[7] = {-0.82, 0.255, -2.7274},
[8] = {0.5, -0.5, 2.7578},
[9] = {0.5, -0.5, -2.578},
[10] = {0.50, 0.084, 2.754},
[11] = {0.50, 0.084, -2.7534},
}, -- end of fires_pos
detection_range_max = 0, --is the max range in kilometers that the radar can see something large (e.g. a bomber, tanker, AWACS, etc.).
radar_can_see_ground = false, -- ground target identification capability, but this has not been verified
CanopyGeometry = { -- Mk1 eyeball sensor for visual spotting targets
azimuth = {-160.0, 160.0}, -- pilot view horizontal (AI)
elevation = {-40.0, 90.0} -- pilot view vertical (AI)
},
Sensors = {
},
HumanRadio = {
frequency = 124.0, -- onboard radio, default DCSW frequency, chnl 0
editable = true,
minFrequency = 108.000,
maxFrequency = 399.975,
rangeFrequency = {
{min = 30.0, max = 87.975},
{min = 108.0, max = 173.975},
{min = 225.0, max = 399.975},
},
},
panelRadio = {
[1] = {
name = _("V/UHF COM1 XT-6013"),
range = {
{min = 108.0, max = 117.975},
{min = 118.0, max = 136.99167},
{min = 137.0, max = 173.975},
{min = 225.0, max = 399.975},
},
channels = {
[1] = { name = _("Channel 1"), default = 225.0, modulation = _("AM")}, -- default
[2] = { name = _("Channel 2"), default = 258.0, modulation = _("AM")},
[3] = { name = _("Channel 3"), default = 260.0, modulation = _("AM")},
[4] = { name = _("Channel 4"), default = 270.0, modulation = _("AM")},
[5] = { name = _("Channel 5"), default = 255.0, modulation = _("AM")},
[6] = { name = _("Channel 6"), default = 259.0, modulation = _("AM")},
[7] = { name = _("Channel 7"), default = 262.0, modulation = _("AM")},
[8] = { name = _("Channel 8"), default = 257.0, modulation = _("AM")},
[9] = { name = _("Channel 9"), default = 253.0, modulation = _("AM")},
[10] = { name = _("Channel 10"), default = 263.0, modulation = _("AM")},
}
},
[2] = {
name = _("V/UHF COM1 XT-6313D"), --VHF/UHF
range = {
{min = 108.0, max = 117.975},
{min = 118.0, max = 136.99167},
{min = 137.0, max = 173.975},
{min = 225.0, max = 399.975},
},
channels = {
[1] = { name = _("Channel 1"), default = 225.0, connect = true}, -- default
[2] = { name = _("Channel 2"), default = 258.0},
[3] = { name = _("Channel 3"), default = 260.0},
[4] = { name = _("Channel 4"), default = 270.0},
[5] = { name = _("Channel 5"), default = 255.0},
[6] = { name = _("Channel 6"), default = 259.0},
[7] = { name = _("Channel 7"), default = 262.0},
[8] = { name = _("Channel 8"), default = 257.0},
[9] = { name = _("Channel 9"), default = 253.0},
[10] = { name = _("Channel 10"), default = 263.0},
}
},
},
-- Countermeasures
SingleChargeTotal = 60,
CMDS_Incrementation = 15,
ChaffDefault = 30,
ChaffChargeSize = 1,
FlareDefault = 15,
FlareChargeSize = 2,
CMDS_Edit = false,
chaff_flare_dispenser = {
[1] =
{
dir = {-1, 0, 0}, -- dispenses to rear
pos = {-6, 0, -0.8}, -- left rear of fuselage
}, -- end of [1]
}, -- end of chaff_flare_dispenser
Pylons = {
pylon(1, 0, -0.200, -0.90, -3.273,
{
connector = 'pylon1', arg = 308 ,arg_value = 0,
use_full_connector_position = false,
},
{
{ CLSID = "{6CEB49FC-DED8-4DED-B053-E1F033FF72D3}" }, -- AIM-9P
{ CLSID = "{ADD3FAE1-EBF6-4EF9-8EFC-B36B5DDF1E6B}" }, -- Mk-20 Rockeye
{ CLSID = "{90321C8E-7ED1-47D4-A160-E074D5ABD902}" }, -- Mk-81
{ CLSID = "{BCE4E030-38E9-423E-98ED-24BE3DA87C32}" }, -- Mk-82
{ CLSID = "{Mk82SNAKEYE}" }, -- MK82SE
{ CLSID = "{00F5DAC4-0466-4122-998F-B1A298E34113}" }, -- M-117
{ CLSID = "{DB769D48-67D7-42ED-A2BE-108D566C8B1E}" }, -- GBU12
{ CLSID = "{0D33DDAE-524F-4A4E-B5B8-621754FE3ADE}" }, -- GBU16
{ CLSID = "{5335D97A-35A5-4643-9D9B-026C75961E52}" }, -- CBU-97
{ CLSID = "{4F977A2A-CD25-44df-90EF-164BFA2AE72F}" }, -- LAU68-MK156
{ CLSID = "{FD90A1DC-9147-49FA-BF56-CB83EF0BD32B}" }, -- LAU-61 - 19
{ CLSID = "{A021F29D-18AB-4d3e-985C-FC9C60E35E9E}" }, -- LAU-68-M151 High Explosive *7
-- { CLSID = "{CBU_105}" ,arg_increment = 0.0}, -- CBU-105
-- { CLSID = "AGM114x2_OH_58" }, --"AGM-114K * 2"
-- { CLSID = "{GBU_49}" ,arg_increment = 0.10 }, --FRENCH GBU-49
{ CLSID = "<CLEAN>", arg_value = 1 }, -- CLEAN --
}
),
pylon(2, 0, -0.200, -1.0, -2.437,
{
connector = 'pylon2', arg = 309 ,arg_value = 0,
use_full_connector_position = false,
},
{
{ CLSID = "{A-29B TANK}" },
{ CLSID = "{ADD3FAE1-EBF6-4EF9-8EFC-B36B5DDF1E6B}" }, -- Mk-20 Rockeye
{ CLSID = "{90321C8E-7ED1-47D4-A160-E074D5ABD902}" }, -- Mk-81
{ CLSID = "{BCE4E030-38E9-423E-98ED-24BE3DA87C32}" }, -- Mk-82
{ CLSID = "{Mk82SNAKEYE}" }, -- MK82SE
{ CLSID = "{00F5DAC4-0466-4122-998F-B1A298E34113}" }, -- M-117
{ CLSID = "{DB769D48-67D7-42ED-A2BE-108D566C8B1E}" }, -- GBU12
{ CLSID = "{0D33DDAE-524F-4A4E-B5B8-621754FE3ADE}" }, -- GBU16
{ CLSID = "{5335D97A-35A5-4643-9D9B-026C75961E52}" }, -- CBU-97
{ CLSID = "{4F977A2A-CD25-44df-90EF-164BFA2AE72F}" }, -- LAU68-MK156
{ CLSID = "{FD90A1DC-9147-49FA-BF56-CB83EF0BD32B}" }, -- LAU-61 - 19
{ CLSID = "{A021F29D-18AB-4d3e-985C-FC9C60E35E9E}" }, -- LAU-68-M151 High Explosive *7
-- { CLSID = "{CBU_105}" ,arg_increment = 0.0}, -- CBU-105
-- { CLSID = "AGM114x2_OH_58" }, --"AGM-114K * 2"
-- { CLSID = "{GBU_49}" ,arg_increment = 0.10 }, --FRENCH GBU-49
{ CLSID = "<CLEAN>", arg_value = 1 }, -- CLEAN --
}
),
pylon(3, 0, -0.66, -1.236, -0.012,
{
connector = 'pylon3', arg = 310 ,arg_value = 0,
use_full_connector_position = false,
},
{
{ CLSID = "{A-29B TANK}" },
{ CLSID = "{ADD3FAE1-EBF6-4EF9-8EFC-B36B5DDF1E6B}" }, -- Mk-20 Rockeye
{ CLSID = "{90321C8E-7ED1-47D4-A160-E074D5ABD902}" }, -- Mk-81
{ CLSID = "{BCE4E030-38E9-423E-98ED-24BE3DA87C32}" }, -- Mk-82
{ CLSID = "{Mk82SNAKEYE}" }, -- MK82SE
{ CLSID = "{00F5DAC4-0466-4122-998F-B1A298E34113}" }, -- M-117
{ CLSID = "{DB769D48-67D7-42ED-A2BE-108D566C8B1E}" }, -- GBU12
{ CLSID = "{0D33DDAE-524F-4A4E-B5B8-621754FE3ADE}" }, -- GBU16
{ CLSID = "{5335D97A-35A5-4643-9D9B-026C75961E52}" }, -- CBU-97
{ CLSID = "<CLEAN>", arg_value = 1 }, -- CLEAN --
}
),
pylon(4, 0, -0.200, -1.0, 2.415,
{
connector = 'pylon4', arg = 311 ,arg_value = 0,
use_full_connector_position = false,
},
{
{ CLSID = "{A-29B TANK}" },
{ CLSID = "{ADD3FAE1-EBF6-4EF9-8EFC-B36B5DDF1E6B}" }, -- Mk-20 Rockeye
{ CLSID = "{90321C8E-7ED1-47D4-A160-E074D5ABD902}" }, -- Mk-81
{ CLSID = "{BCE4E030-38E9-423E-98ED-24BE3DA87C32}" }, -- Mk-82
{ CLSID = "{Mk82SNAKEYE}" }, -- MK82SE
{ CLSID = "{00F5DAC4-0466-4122-998F-B1A298E34113}" }, -- M-117
{ CLSID = "{DB769D48-67D7-42ED-A2BE-108D566C8B1E}" }, -- GBU12
{ CLSID = "{0D33DDAE-524F-4A4E-B5B8-621754FE3ADE}" }, -- GBU16
{ CLSID = "{5335D97A-35A5-4643-9D9B-026C75961E52}" }, -- CBU-97
{ CLSID = "{4F977A2A-CD25-44df-90EF-164BFA2AE72F}" }, --LAU68-MK156
{ CLSID = "{FD90A1DC-9147-49FA-BF56-CB83EF0BD32B}" }, -- LAU-61 - 19
{ CLSID = "{A021F29D-18AB-4d3e-985C-FC9C60E35E9E}" }, -- LAU-68-M151 High Explosive *7
-- { CLSID = "{CBU_105}" ,arg_increment = 0.0}, -- CBU-105
-- { CLSID = "AGM114x2_OH_58" }, --"AGM-114K * 2"
-- { CLSID = "{GBU_49}" ,arg_increment = 0.10 }, --FRENCH GBU-49
{ CLSID = "<CLEAN>", arg_value = 1 }, -- CLEAN --
}
),
pylon(5, 0, -0.20, -0.9, 3.251,
{
connector = 'pylon5', arg = 312 ,arg_value = 0,
use_full_connector_position = false,
},
{
{ CLSID = "{6CEB49FC-DED8-4DED-B053-E1F033FF72D3}" }, -- AIM-9P
{ CLSID = "{ADD3FAE1-EBF6-4EF9-8EFC-B36B5DDF1E6B}" }, -- Mk-20 Rockeye
{ CLSID = "{90321C8E-7ED1-47D4-A160-E074D5ABD902}" }, -- Mk-81
{ CLSID = "{BCE4E030-38E9-423E-98ED-24BE3DA87C32}" }, -- Mk-82
{ CLSID = "{Mk82SNAKEYE}" }, -- MK82SE
{ CLSID = "{00F5DAC4-0466-4122-998F-B1A298E34113}" }, -- M-117
{ CLSID = "{DB769D48-67D7-42ED-A2BE-108D566C8B1E}" }, -- GBU12
{ CLSID = "{0D33DDAE-524F-4A4E-B5B8-621754FE3ADE}" }, -- GBU16
{ CLSID = "{5335D97A-35A5-4643-9D9B-026C75961E52}" }, -- CBU-97
{ CLSID = "{4F977A2A-CD25-44df-90EF-164BFA2AE72F}" }, --LAU68-MK156
{ CLSID = "{FD90A1DC-9147-49FA-BF56-CB83EF0BD32B}" }, -- LAU-61 - 19
{ CLSID = "{A021F29D-18AB-4d3e-985C-FC9C60E35E9E}" }, -- LAU-68-M151 High Explosive *7
-- { CLSID = "{CBU_105}" ,arg_increment = 0.0}, -- CBU-105
-- { CLSID = "AGM114x2_OH_58" }, --"AGM-114K * 2"
-- { CLSID = "{GBU_49}" ,arg_increment = 0.10 }, --FRENCH GBU-49
{ CLSID = "<CLEAN>", arg_value = 1 }, -- CLEAN --
}
),
pylon(6, 0, 1.0, -1.13, 0.0,
{
connector = 'flir',
use_full_connector_position = false,
DisplayName = "FLIR",
},
{
{ CLSID = "{FLIR-STAR-SAFIRE}" },
{ CLSID = "<CLEAN>", arg_value = 1 }, -- CLEAN --
}
),
pylon(7, 0, 1.664, -0.933, 0.715,
{
use_full_connector_position = true,
connector = "SmokeWhite",
DisplayName = "Smoke",
},
{
{CLSID = "{SMOKE-WHITE-A29B}", arg_value = 0.2}, -- Smoke pod
{CLSID = "{SMOKE-RED-A29B}", arg_value = 0.2}, -- Smoke pod
{CLSID = "{SMOKE-GREEN-A29B}", arg_value = 0.2}, -- Smoke pod
{CLSID = "{SMOKE-BLACK-A29B}", arg_value = 0.2}, -- Smoke pod
{CLSID = "{SMOKE-ORANGE-A29B}", arg_value = 0.2}, -- Smoke pod
{CLSID = "{SMOKE-YELLOW-A29B}", arg_value = 0.2}, -- Smoke pod
}
),
},
Tasks = {
aircraft_task(CAP),
aircraft_task(Escort),
aircraft_task(FighterSweep),
aircraft_task(GroundAttack),
aircraft_task(PinpointStrike),
aircraft_task(CAS),
aircraft_task(AFAC),
aircraft_task(RunwayAttack),
aircraft_task(AntishipStrike),
aircraft_task(Intercept),
},
DefaultTask = aircraft_task(CAS),
-- AirframeProperties =
-- {
-- foreplane =
-- {
-- area = 6.70; -- in square meters
-- span = 5.45; -- in meters
-- mean_chord = 2.3; -- mean aerodynamic chord length
-- mean_chord_position = 1.0; -- mean aerodynamic chord position
-- mean_chord_position_y = 1.0; -- mean aerodynamic chord position - vertical
-- sweep_angle = 59; -- for leading edge
-- sweep_angle_25 = 59; -- 25 % of the way back from the leading edge
-- tip_pos = {1.35, -0.02, -2.42}; -- for vortex attachment
-- },
-- },
-- center_of_mass = { empty_cg_position , spinner_tip_position[2] , 0.0}, -- center of mass position relative to object 3d model center for empty aircraft
-- moment_of_inertia = {14056.0, 40927.0, 30700.0}, -- moment of inertia of empty aircraft
SFM_Data = {
aerodynamics =
{
Cy0 = 0.1933, -- Coefficient of lift at zero angle of attack -- Always 0 for symmetrical airfoil
Mzalfa = 4.355, -- Horizontal tail pitch coefficient
Mzalfadt = 0.8, -- Wing pitch coefficient
kjx = 2.25, -- Roll rate dampening
kjz = 0.00125, -- Pitch rate dampening
Czbe = -0.056, -- Directional stability coefficient -- coefficient, along Z axis (perpendicular), affects yaw, negative value means force orientation in FC coordinate system
cx_gear = 0.0277, -- Additional coefficient of drag for gear extended
cx_flap = 0.095, -- Additional coefficient of drag for flap extended
cy_flap = 0.18, -- Additional coefficient of lift for flap extended
cx_brk = 0.065, -- Additional coefficient of drag for air brakes
-- mz_table_data
-- mz_ige_table_data
-- mx_table_data
-- Hi guys. I try to calculate the rollrate, or maxrollrate (omxmax) for a plane and I've got the measurements of the plane, Cl (rolling moment coefficient) and Clp.
-- I've found a formula for Rollrate which looks like this:
-- rollrate = -((2 * v) / b) * (Cle / Clp) * ((Eleft - Eright) / 2)
-- v is (obiously) speed, b is wingspan, Cle coefficient of rolling moment due to aileron deflection, Clp coefficient of rolling dampening, E is the aileron deflection angle
-- If it Rolls to fast then decrease Omxmax. If The rollaccelleration is to quick, lower kjx.
table_data =
{
-- M - Mach number
-- Cx0 - Coefficient of drag for zero lift -- Coefficient, drag, profile, of the airplane
-- Cya - Coefficient of lift for angle of attack -- Normal force coefficient of the wing and body of the aircraft in the normal direction to that of flight. Inversely proportional to the available G-loading at any Mach value. (lower the Cya value, higher G available) per 1 degree AOA
-- B - Induced drag factor -- Polar quad coeff
-- B4 - Viscous drag factor --Polar 4th power coeff
-- Omxmax - Roll rate - roll rate, rad/s
-- Aldop - Stall AOA at current M
-- Cymax - Maximum coefficient of lift, corresponding to αstall -- Coefficient, lift, maximum possible (ignores other calculations if current Cy > Cymax)
-- Cold start sound.
-- Park breaking lights.
-- NP 100%
-- AP entra em R/P
-- Guns piper baixo 5 mils
-- The variables "B" and "B4" in the SFM of DCS are "modifiers" of the variable "drag at zero Lift" aka Cx0 to make those values fit the Lift/Drag (or Drag/Lift)-Polars,
-- where at the same mach-speed different values of drag (CD) are possible due to different angles of attack "AoA" (see above chart in post at 15h18 07.02.2021).
-- This is necessary, since the SFM does not differentiate between different angles of attack, but has to take into account, that a plane at 15° AoA has a lot more drag than
-- one at 1°AoA. The basic formula is
-- CD = Cx0 + B * CL^2 + B4 * CL^4
-- CD is the "total" Drag at the given Speed, in NASA-Papers CD. Cx0 is drag at zero lift, in NASA-Papers CDmin.
-- CL is Lift at given speeds, in NASA-Papers CL, which is once squared and once put to the 4th power for the formula. B on the other hand is also known as K which is
-- 1 / (pi * AR * e). pi needs no explanation, since it is the number pi. AR is the aspect-ratio of the wing which is AR = S^2 / A where S is the Wingspan and A is the wing area.
-- e is the "Oswald Factor" or "wing-efficiency-factor" which is somewhere between 0.7 and 1.0. If you take 0.7 for landing speeds and take-off speeds,
-- where flaps and gear is extended, you will be approx. right, for everything else 0.85 or 0.9 is a good guess.
-- So if you have a NASA-Report or something like that, the only unknown might be B4. If you solve the equation for B4 it looks like this:
-- B4 = (-Cx0 - B * CL^2 + CD) / CL^4
-- CL = Cy0 + AoA * Cya
-- When angle-of-attack (a) is below Aldop:
-- Cy(M,a) = Cy0 + Cya(M)*a
-- in other words B4 = (-CDmin - (1 / pi * AR * e) * CL^2 + CD) / CL^4
-- Just thought about B and B4 a bit more and forgot that you have to add wave-drag for those speeds, where the wing is supersonic.
-- Wave-Drag = CDwave = a * ((Mach / Mach-crit) - 1)^b. Now comes the problem what is "a" and "b"?
-- From this: https://www.fzt.haw-hamburg.de/pers/Scholz/HOOU/AircraftDesign_13_Drag.pdf you could see, that a and b are given (or already calculated) for a few aircrafts.
-- You can calculate it yourself, and have fun with this: https://www.fzt.haw-hamburg.de/pers/Scholz/materialFM1/DragEstimation.pdf or you can go the easy way and "simplify"
-- it a bit more by saying that a fighter-jet as an "a" of 0.8 and a "b" of 2.6. A piston-driven aircraft has a = 0.02 and b = 2.20 and a jet driven cargo-plane has a = 1.2
-- and b = 3.9. Than you need Mach-crit (Mcrit) which can, again be calculated (see above) or, for simplicity for a fighter-jet Mcrit = 0.9, Piston-plane Mcrit = 0.5 and
-- Cargo-Plane Mcrit = 0.625. Now you just have to ad CDwave to the equation for B. It will look like this: B = (CDwave + 1) / (pi * A * e). Of course, you "ad" CDwave
-- only at speeds above Mcrit, because at Mcrit it will be 0.
-- And on another thought, e (the wing-efficiency-factor) is more likely something between 0.75 and 0.85 for fighter Planes, where 0.75 is not so efficient and 0.85 is
-- more efficient. The shorter, thicker the wing, the more unefficient (I would say/guess or whatever)...or you can calculate it (see above) which looks like a
-- nicely spent weekend to me
-- M Cx0 Cya B B4 Omxmax Aldop Cymax
{0 /666.739, 0.0708, 0.0880, 0.0069, 0.1382, 0.15, 18, 1.7771, },
{10 /666.739, 0.0708, 0.0880, 0.0069, 0.1382, 0.20, 18, 1.7771, },
{30 /666.739, 0.0708, 0.0880, 0.0069, 0.1382, 0.30, 18, 1.7771, },
{50 /666.739, 0.0708, 0.0880, 0.0069, 0.1382, 0.40, 18, 1.7771, },
{70 /666.739, 0.0708, 0.0880, 0.0069, 0.1382, 0.50, 18, 1.7771, },
{80 /666.739, 0.0708, 0.0880, 0.0069, 0.1382, 0.55, 18, 1.7771, },
{90 /666.739, 0.0708, 0.0880, 0.0069, 0.1382, 0.60, 18, 1.7771, },
{100/666.739, 0.0708, 0.0880, 0.0069, 0.1382, 0.65, 18, 1.7771, },
{110/666.739, 0.0708, 0.0880, 0.0069, 0.1382, 0.70, 18, 1.7771, },
{130/666.739, 0.0708, 0.0807, 0.0069, 0.1382, 0.90, 18, 1.6462, },
{150/666.739, 0.0708, 0.0770, 0.0069, 0.1382, 1.2, 18, 1.5798, },
{170/666.739, 0.0708, 0.0759, 0.0069, 0.1382, 1.2, 18, 1.5596, },
{190/666.739, 0.0708, 0.0761, 0.0069, 0.1382, 1.6, 18, 1.5629, },
{210/666.739, 0.0708, 0.0756, 0.0069, 0.1382, 2.1, 18, 1.5542, },
{220/666.739, 0.0708, 0.0798, 0.0069, 0.1382, 2.1, 18, 1.6250, },
{230/666.739, 0.0708, 0.0841, 0.0069, 0.1382, 2.1, 18, 1.7063, },
{240/666.739, 0.0708, 0.0853, 0.0069, 0.1382, 2.6, 17, 1.7250, },
{250/666.739, 0.0708, 0.0866, 0.0069, 0.1382, 2.6, 16, 1.7514, },
{270/666.739, 0.0708, 0.0864, 0.0069, 0.1382, 2.6, 15, 1.7476, },
{290/666.739, 0.0708, 0.0964, 0.0069, 0.1382, 3.1, 14, 1.9293, },
{310/666.739, 0.0708, 0.1054, 0.0069, 0.1382, 3.5, 12, 2.0907, },
{360/666.739, 0.0708, 0.1054, 0.0069, 0.1382, 3.5, 7, 2.0907 },
{600/666.739, 0.0708, 0.1054, 0.0069, 0.1382, 3.5, 1, 2.0907 },
}
}, -- end of aerodynamics
engine =
{
Nmg = 64.6, -- % RPM at idle
MinRUD = 0, -- always 0 in current modeled aircraft -- Min state of the throttle
MaxRUD = 1, -- always 1 in current modeled aircraft -- Max state of the throttle
MaksRUD = 1, -- .85 for afterburning, 1 for non-afterburning engine. -- Military power state of the throttle
ForsRUD = 1, -- .91 for afterburning, 1 for non-afterburning -- Afterburner state of the throttle
typeng = 3, -- E_TURBOJET = 0, E_TURBOJET_AB = 1, E_PISTON = 2, E_TURBOPROP = 3, E_TURBOFAN = 4, E_TURBOSHAFT = 5
hMaxEng = 19.5, -- maximum operating altitude for the engine in km -- typically higher than service ceiling of the aircraft
dcx_eng = 0.095, -- drag coefficient for the engine -- no correlation found -- most common values are 0.0085 and 0.0144
cemax = 0.37, -- not used for fuel calculation , only for AI routines to check flight time ( fuel calculation algorithm is built in )
cefor = 0.37, -- not used for fuel calculation , only for AI routines to check flight time ( fuel calculation algorithm is built in )
dpdh_m = 1800, -- altitude coefficient for max thrust -- altitude effects to thrust -- The best recommendation at this point is to start with these values between 2000 and 3000 and adjust as needed after initial flight testing
dpdh_f = 1800, -- altitude coefficient for AB thrust ???? or altitude effects to fuel rate -- The best recommendation at this point is to start with these values between 2000 and 3000 and adjust as needed after initial flight testing
prop_locations = {{3.149, -0.524 , 0.014}, {0.0, 0.0, math.rad(-1.87)},},
prop_blades_count = 5,
prop_pitch_min = 23.0, -- prop pitch min, degrees
prop_pitch_max = 65.0, -- prop pitch max, degrees
prop_pitch_feather = 80.0, -- prop pitch feather position, degrees if feather < prop_pitch_max no feathering available
Nominal_RPM = 30000,
Nominal_Fan_RPM = 2000,
Startup_RPMs = {
{0.0, 0},
{1.0, 60},
{8.0, 60},
{8.6, 880},
{13.0, 601},
},
Startup_Prework = 1.0,
Startup_Ignition_Time = 8.3,
Shutdown_Duration = 9.8,
table_data = {
-- Pmax - total thrust in Mil Pwr in Newtons for all engines
-- Pfor - total thrust in AB in Newtons for all engines
-- M Pmax Pfor
{0.0, 16620.0},
{0.1, 15600.0},
{0.2, 14340.0},
{0.3, 13320.0},
{0.4, 12230.0},
{0.5, 11300.0},
{0.6, 10600.0},
{0.7, 10050.0},
{0.8, 9820.0},
{0.9, 5902.0},
{1.0, 3469.0}
},
-- M - Mach number
-- Pmax - Engine thrust at military power
-- Pfor - Engine thrust at AFB
extended = {
thrust_max = -- thrust interpolation table by altitude and mach number, 2d table
{ -- Minimum thrust 2000 kN, maximum thrust 16700 kN
M = {0/666.739,100/666.739,120/666.739,140/666.739,160/666.739,200/666.739,220/666.739,280/666.739,320/666.739,400/666.739},
H = {0,3048,6096,9144,10500,12192},
thrust = {--KCAS 0 100 120 140 160 200 220 280 320 400
{ 17000, 17000, 17000, 17000, 17000, 17000, 17000, 17000, 16925, 17000 },--H = 0 (sea level)
{ 16000, 16000, 16000, 16000, 16000, 16000, 16000, 16000, 16000, 16000 },--H = 3048 (10kft)
{ 11500, 11500, 11500, 11500, 11500, 11500, 11500, 11500, 11500, 11500 },--H = 6096 (20kft)
{ 7000, 7000, 7000, 7000, 7000, 7000, 7000, 7000, 7000, 7000 },--H = 9144 (30kft)
{ 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000 },--H = 10500 (34kft)
{ 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000 },--H = 12192 (40kft)
},
},
TSFC_max = -- thrust specific fuel consumption by altitude and Mach number for RPM 100%, 2d table
{ -- factor = kg/h /2000
M = {0/666.739, 140/666.739, 160/666.739, 200/666.739, 220/666.739, 260/666.739, 300/666.739},
H = {0, 1524, 3048, 4572, 6096, 7620, 9144},
TSFC = {-- KT 0 140 160 200 220 260 300--0.1264
{ 150/1800, 195/1800, 205/1800, 243/1800, 271/1800, 347/1800, 380/1800},--H = 0 -- SL
{ 140/1800, 180/1800, 188/1800, 218/1800, 240/1800, 300/1800, 360/1800},--H = 1524 -- 5000'
{ 130/1800, 152/1800, 175/1800, 195/1800, 215/1800, 268/1800, 330/1800},--H = 3048 -- 10000'
{ 120/1800, 120/1800, 160/1800, 177/1800, 191/1800, 234/1800, 285/1800},--H = 4572 -- 15000'
{ 115/1800, 115/1800, 135/1800, 165/1800, 175/1800, 210/1800, 250/1800},--H = 6096 -- 20000'
{ 110/1800, 110/1800, 110/1800, 160/1800, 165/1800, 195/1800, 210/1800},--H = 7620 -- 25000'
{ 110/1800, 110/1800, 110/1800, 152/1800, 165/1800, 175/1800, 175/1800},--H = 9144 -- 30000'
}
},
-- TSFC_afterburner = -- thrust specific fuel consumption by altitude and Mach number for RPM 100%, 2d table
-- { -- factor = kg/h /2000
-- M = {0/666.739, 140/666.739, 160/666.739, 200/666.739, 220/666.739, 260/666.739, 300/666.739},
-- H = {0, 1524, 3048, 4572, 6096, 7620, 9144},
-- TSFC = {-- KT 0 140 160 200 220 260 300--0.1264
-- { 150/1800, 195/1800, 205/1800, 243/1800, 271/1800, 347/1800, 380/1800},--H = 0 -- SL
-- { 140/1800, 180/1800, 188/1800, 218/1800, 240/1800, 300/1800, 360/1800},--H = 1524 -- 5000'
-- { 130/1800, 152/1800, 175/1800, 195/1800, 215/1800, 268/1800, 330/1800},--H = 3048 -- 10000'
-- { 120/1800, 120/1800, 160/1800, 177/1800, 191/1800, 234/1800, 285/1800},--H = 4572 -- 15000'
-- { 115/1800, 115/1800, 135/1800, 165/1800, 175/1800, 210/1800, 250/1800},--H = 6096 -- 20000'
-- { 110/1800, 110/1800, 110/1800, 160/1800, 165/1800, 195/1800, 210/1800},--H = 7620 -- 25000'
-- { 110/1800, 110/1800, 110/1800, 152/1800, 165/1800, 175/1800, 175/1800},--H = 9144 -- 30000'
-- }
-- },
TSFC_throttle_responce = -- correction to TSFC for different engine RPM, 1d table
{
RPM = {0, 70, 80, 90, 100},
K = {1, 1, 1, 1, 1},
},
-- thrust_afterburner = -- thrust interpolation table by altitude and mach number, 2d table
-- { -- Minimum thrust 2000 kN, maximum thrust 16700 kN
-- M = {0*666.739,100*666.739,120*666.739,140*666.739,160*666.739,200*666.739,220*666.739,280*666.739,320*666.739,400*666.739},
-- H = {0,3048,6096,9144,10500,12192},
-- thrust = {--KCAS 0 100 120 140 160 200 220 280 320 400
-- { 17000, 17000, 17000, 17000, 17000, 17000, 17000, 17000, 16925, 17000 },--H = 0 (sea level)
-- { 16000, 16000, 16000, 16000, 16000, 16000, 16000, 16000, 16000, 16000 },--H = 3048 (10kft)
-- { 11500, 11500, 11500, 11500, 11500, 11500, 11500, 11500, 11500, 11500 },--H = 6096 (20kft)
-- { 7000, 7000, 7000, 7000, 7000, 7000, 7000, 7000, 7000, 7000 },--H = 9144 (30kft)
-- { 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000 },--H = 10500 (34kft)
-- { 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000, 5000 },--H = 12192 (40kft)
-- },
-- },
rpm_acceleration_time_factor = -- time factor for engine governor ie RPM += (desired_RPM - RPM ) * t(RPM) * dt
{
RPM = {0, 50, 100},
t = {0.9,0.9,0.9}
},
--rpm_deceleration_time_factor = -- time factor for engine governor
--{
-- RPM = {0, 50, 100},
-- t = {0.3,0.3,0.3}
--},
rpm_throttle_responce = -- required RPM according to throttle position
{
throttle = {0, 0.1, 0.55, 1.0},
RPM = {64.6, 84, 92, 100},
},
thrust_rpm_responce = -- thrust = K(RPM) * thrust_max(M,H)
{
RPM = {0, 64.6, 84, 100},
K = {0, 0.00, 0.1, 1},
},
}, -- end of extended data
}, -- end of engine
-- engine_data = {
-- power_take_off = 1000.0 * algumacoisa,
-- power_max = 1000.0 * algumacoisa,
-- power_WEP = algumacoisa,
-- power_TH_k = algumacoisa,
-- SFC_k = 0,
-- power_RPM_k = 0,
-- power_RPM_min = 0,
-- Nmg_Ready = 0,
-- },
},
AddPropAircraft = {
{
id = "SoloFlight",
control = 'checkbox',
label = _('Solo Flight'),
defValue = false,
weightWhenOn = -80,
wCtrl = 150,
},
{ id = "NetCrewControlPriority" , control = 'comboList', label = _('Aircraft Control Priority'), playerOnly = true,
values = {{id = 0, dispName = _("Pilot")},
{id = 1, dispName = _("Instructor")},
{id = -1, dispName = _("Ask Always")},
{id = -2, dispName = _("Equally Responsible")}},
defValue = 1,
wCtrl = 150
},
},
DamageParts =
{
[1] = "A-29B-collision", -- wing R
},
Failures = {
{ id = 'asc', label = _('ASC'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'autopilot', label = _('AUTOPILOT'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'hydro', label = _('HYDRO'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'l_engine', label = _('L-ENGINE'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'r_engine', label = _('R-ENGINE'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'radar', label = _('RADAR'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'eos', label = _('EOS'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'helmet', label = _('HELMET'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
--{ id = 'mlws', label = _('MLWS'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'rws', label = _('RWS'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'ecm', label = _('ECM'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'hud', label = _('HUD'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
{ id = 'mfd', label = _('MFD'), enable = false, hh = 0, mm = 0, mmint = 1, prob = 100 },
},
--damage , index meaning see in Scripts\Aircrafts\_Common\Damage.lua
Damage = {
[0] = {critical_damage = 5, args = {146}},
[3] = {critical_damage = 20,args = {65}} ,
[4] = {critical_damage = 20, args = {150}},
[5] = {critical_damage = 20, args = {147}},
[7] = {critical_damage = 4, args = {249}} ,
[9] = {critical_damage = 3, args = {154}},
[10] = {critical_damage = 3, args = {153}},
[11] = {critical_damage = 3, args = {167}},
[12] = {critical_damage = 3, args = {161}},
[15] = {critical_damage = 5, args = {267}},
[16] = {critical_damage = 5, args = {266}},
[23] = {critical_damage = 8, args = {223}, deps_cells = {25}},
[24] = {critical_damage = 8, args = {213}, deps_cells = {26, 60}},
[25] = {critical_damage = 3, args = {226}},
[26] = {critical_damage = 3, args = {216}},
[29] = {critical_damage = 9, args = {224}, deps_cells = {31, 25, 23}},
[30] = {critical_damage = 9, args = {214}, deps_cells = {32, 26, 24, 60}},
[31] = {critical_damage = 4, args = {229}},
[32] = {critical_damage = 4, args = {219}},
[35] = {critical_damage = 10, args = {225}, deps_cells = {29, 31, 25, 23}},
[36] = {critical_damage = 10, args = {215}, deps_cells = {30, 32, 26, 24, 60}} ,
[37] = {critical_damage = 4, args = {227}},
[38] = {critical_damage = 4, args = {217}},
[39] = {critical_damage = 7, args = {244}, deps_cells = {53}},
[40] = {critical_damage = 7, args = {241}, deps_cells = {54}},
[45] = {critical_damage = 9, args = {235}, deps_cells = {39, 51, 53}},
[46] = {critical_damage = 9, args = {233}, deps_cells = {40, 52, 54}},
[51] = {critical_damage = 3, args = {239}},
[52] = {critical_damage = 3, args = {237}},
[53] = {critical_damage = 3, args = {248}},
[54] = {critical_damage = 3, args = {247}},
[55] = {critical_damage = 20, args = {81}, deps_cells = {39, 40, 45, 46, 51, 52, 53, 54}},
[59] = {critical_damage = 5, args = {148}},
[60] = {critical_damage = 1, args = {144}},
[83] = {critical_damage = 3, args = {134}} ,-- nose wheel
[84] = {critical_damage = 3, args = {136}}, -- left wheel
[85] = {critical_damage = 3, args = {135}} ,-- right wheel
},
lights_data = {
typename = "collection",
lights = {
[WOLALIGHT_STROBES] = {
typename = "collection",
lights = {
{ typename = "argnatostrobelight", argument = 83, period = 1.2}, -- beacon lights
},
},--must be collection
[WOLALIGHT_LANDING_LIGHTS] = {
typename = "collection",
lights = {
{ typename = "argumentlight", argument = 51, },
},
},--must be collection
[WOLALIGHT_TAXI_LIGHTS] = {
typename = "collection",
lights = {
{ typename = "argumentlight", argument = 208, },
},
},--must be collection
[WOLALIGHT_NAVLIGHTS] = {
typename = "collection",
lights = {
{ typename = "argumentlight", argument = 49, }, -- red
},
},--must be collection
[WOLALIGHT_FORMATION_LIGHTS] = {
typename = "collection",
lights = {
{ typename = "argumentlight", argument = 88, },
}, -- green bars
},--must be collection
-- STROBE / ANTI-COLLISION
[WOLALIGHT_BEACONS] = {
typename = "collection",
lights = {
-- 0 -- Anti-collision strobe
{ typename = "argnatostrobelight", argument = 200, period = 0.4, flash_time = 0.1, },
},
},
}
},
stores_number = 10,
LandRWCategories =
{
[1] =
{
Name = "AircraftCarrier",
}, -- end of [1]
}, -- end of LandRWCategories
MaxFuelWeight = "15245",
MaxHeight = "20000",
MaxSpeed = "3000",
MaxTakeOffWeight = "41200",
Picture = "A-29B.png",
Rate = "30",
Shape = "A-29B",
TakeOffRWCategories =
{
[1] =
{
Name = "AircraftCarrier With Catapult",
}, -- end of [1]
[2] =
{
Name = "AircraftCarrier With Tramplin",
}, -- end of [2]
}, -- end of TakeOffRWCategories
Countermeasures = {
ECM = "AN/ALQ-165"
},
passivCounterm = {
CMDS_Edit = true,
SingleChargeTotal = 60,
chaff = {default = 30, increment = 1, chargeSz = 1},
flare = {default = 30, increment = 1, chargeSz = 1},
},
chaff_flare_dispenser = {
{ dir = {0, -1, 0}, pos = {-3.027, 0.35, -0.3}, }, -- Chaff L
{ dir = {0, -1, 0}, pos = {-3.727, 0.35, 0.3}, }, -- Chaff R
{ dir = {0, -1, 0}, pos = {-3.032, 0.35, -0.32}, }, -- Flares L
{ dir = {0, -1, 0}, pos = {-3.732, 0.35, 0.32}, }, -- Flares R
},
mapclasskey = "P0091000024",
Guns = {
MG_20({muzzle_pos = {0.82,-0.705, 2.326},_connector = "Point_Gun_01_R",rates = {1025},effect_arg_number = 350,mixes = {{1,2,2,3,3}},azimuth_initial = 0.0,elevation_initial = 0,supply_position = {4.5,0.22, 0.3}}),-- MITRAIL AVR 1
MG_20({muzzle_pos = {0.82, -0.705, -2.326},_connector = "Point_Gun_01_L",rates = {1025},effect_arg_number = 436,mixes = {{1,2,2,3,3}},azimuth_initial = 0.0,elevation_initial = 0,supply_position = {2.0, -0.25, 0.8}}),-- MITRAIL AVR 2 B
}, -- 3dsmax X, Z, -Y
}
add_aircraft(A_29B)