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Concorde.xml
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<?xml version="1.0"?>
<?xml-stylesheet href="http://jsbsim.sourceforge.net/JSBSim.xsl" type="text/xsl"?>
<fdm_config name="Aerospatiale/BAC Concorde" version="2.0" release="PRODUCTION"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> </author>
<filecreationdate> 5 June 2015 </filecreationdate>
<version> 2.20 </version>
<description>Aérospatiale-BAC Concorde is a turbojet-powered supersonic passenger jet airliner that was in service from 1976 to 2003. It is one of only two supersonic transports to have entered commercial service; the other was the Tupolev Tu-144. Concorde was jointly developed and produced by Aérospatiale and the British Aircraft Corporation (BAC) under an Anglo-French treaty. It featured a maximum speed over twice the speed of sound at Mach 2.04, with seating for 92 to 128 passengers. First flown in 1969, Concorde entered service in 1976 and continued commercial flights for 27 years.</description>
<license>
<licenseName>GPL (General Public License)</licenseName>
<licenseURL>http://www.gnu.org/licenses/gpl.html</licenseURL>
</license>
<note>Nose gear is longer.</note>
<note>Air intake effect, which allows more drag at Mach 1.3-2.0.</note>
<note>Full tanks at maximum takeoff load.</note>
<note>Tanks with dissymmetry.</note>
<note>Landing pitch is 10 deg (maximum landing load) and ground effect.</note>
<note>Climb pitch at 10 deg (maximum landing load).</note>
<note>Climb Mach 0.95 to 1.7 in 10 minutes.</note>
<note>Weaker supersonic lift</note>
<note>Can reach Mach 2.0, below the VMO.</note>
<note>Inside of center of gravity corridor.</note>
<note>Shift of center of pressure.</note>
<note>London - New York : lands below max landing weight (aloft westerly at 39 kt).</note>
<note>Gear height adjusted by 3D model, supposed accurate.</note>
<note>Pushback.</note>
<limitation>Model uses flaps as nose.</limitation>
<limitation>Cross feed by additional tanks :
engine may run out of fuel above X 3 speed-up.</limitation>
<limitation>Without an additional PID, above Mach 1,
autopilot heading hold would lock with a right roll.</limitation>
<limitation>Air intake failure only on the 4 engines at once.</limitation>
<limitation>Ground idle only on the 4 engines at once.</limitation>
<!--
File: Concorde.xml
Author: Aero-Matic v 0.71
Inputs:
name: Concorde
type: four-engine transonic transport
max weight: 408000 lb
wing span: 83.83 ft
length: 202.33 ft
wing area: 3856 sq-ft
gear type: tricycle
retractable?: yes
# engines: 4
engine type: turbine
engine layout: wings
yaw damper? yes
Outputs:
wing loading: 105.81 lb/sq-ft
CL-alpha: 4.4 per radian
CL-0: 0.2
CL-max: 1.2
CD-0: 0.017
K: 0.042
-->
<note>notation : "=>" denotes a final choice based on certain real values.</note>
<reference
refID="FAA certificate, A45eu"
author="FAA"
title="http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet"
date="9 January 1979"/>
<documentation>
Vlo (landing gear operation) : 270 kt.
Vle (landing gear extended) : 270 kt.
Vmc (minimum control speed with engine inoperative)
Vmcl (approach) : 150 kt.
Vmc (takeoff) : 132 kt.
Vmcg (ground) : 116 kt.
Datum : the datum for center of gravity computation is a vertical
reference plane located 8.333 feet (2.540 m) forward of Fuselage
Station X.A.0. A reference rigging point "C" is provided on the
airframe 83.172 feet (25.351 m) aft of the datum at 13.66% C0.
M.A.C. : the "reference root choord" (C0) is 90.748 feet (27.660 m) in
length; its leading edge is located 70.771 feet (21.570 m) aft of the datum.
Fuel tank capacity (at density 6.68 lb / US Gallon) :
Tank Usable weight Total weight Arm (% MAC)
........................................................
1 9348 9361 39.80
2 10176 10207 76.10
3 10176 10207 76.10
4 9348 9361 39.80
5 16032 16072 49.40
5A 4956 4963 74.80
6 25803 25889 66.70
7 16490 16525 64.70
7A 4956 4963 74.80
8 28590 28645 46.70
9 24710 24747 16.90
10 26597 26618 30.50
11 23192 23218 113.90
Systems 827 1021 69.43
........................................................
Totals 211200 lb 211797 lb 56.23
</documentation>
<documentation>
- http://perso.wanadoo.fr/hsors/FS_Soft/FAQ-FS2K2-Decode_Forum.txt/
Ron Freimuth (for MSFS) :
TYPE OF AIRCRAFT - ROLL,Rx PITCH,Ry YAW,Rz
Single Low Wing .248 .338 .393
Single High Wing(C182R) .242 .397 .393
Light Twin .373 .269 .461
Biz Jet, Light .293 .312 .420
Biz Jet, Heavy .370 .356 .503
Twin Turbo- Prop .235 .363 .416
Jet Airliner 4 eng. .322 .339 .464
Jet Airliner 3 aft eng .249 .375 .452
Jet Airliner 2 eng wing .246 .382 .456
Prop Airliner 4 eng .322 .324 .456
Prop Airliner 2 eng .308 .345 .497
Jet Fighter .266 .346 .400
Prop Fighter 1 eng .268 .360 .420
Prop Fighter 2 eng .330 .299 .447
Prop Bomber 2 eng .270 .320 .410
Prop Bomber 4 eng .316 .320 .376
Concorde Delta Wing .255 .380 .390 (added, Ron Freimuth)
Note: Delta Wing adds more to Pitch MoI due to Long Root Chord.
Note: Yaw MoI ~ Pitch MoI + Roll MoI or a bit less.
... Estimate Aircraft Moments of Inertia - from Jan Roskam ...
Roll Ixx = (W/g)*(Rx*b/2)^2
Pitch Iyy = (W/g)*(Ry*d/2)^2
Yaw Izz = (W/g)*(Rz*e/2)^2
Roll-Yaw Ixz less than or equal to 0.02 Iz, often 0.0 (added, Ron Freimuth)
g = 32.174 ft/s^2
W = gross wt. lb
b = span ft
d = length ft
e = (b+d)/2
Max TO - 408,000 lb
No Fuel - 197,768 lb
Length - 204.5 ft (.38*102)^2 = 1502
Span - 84.25 ft (.253*42)^2
= 113(Span+Length)/2 - 144.8 ft (.39*72.4)^2 = 797
Width - 9.5 ft
Empty Mass - 197,768/32.174 = 6,142 slugs
Max Mass - 408,000/32.174 = 12,670 slugs
.... Empty
Pitch: 1502 * 6142 = 9,227,000, Max: 19,034,000 slug ft^2
Roll: 113 * 6142 = 694,000, Max: 1,432,000
Yaw: 797 * 6142 = 4,897,000, Max: 10,100,000
Pitch is about 9,300,000, Yaw is 4,900,000, Roll is 696,000.
The moments of inertia had been changed, as an attempt to solve the autopilot roll.
</documentation>
<documentation>
- http://www.concordesst.com/ :
Length : overall 202'4", nose to cockpit 24'.
Height : fuselage max external 10'10".
Width : fuselage max external 9'5".
Gear : main track 25'4".
Wing : span 83 ft. 10 in., length (root chord) 90 ft. 9 in..
Area (sq. ft) : Wing 3856, Elevon (each side) 172.2, Tail 365, Rudder 112.
Weight (lbs) : max take off 408000, zero fuel 203000, operating empty 173500,
max payload 29500, max taxing 412000, max landing 245000.
Fuel : max 26400 gallons.
TABLE A :
Fuel tanks tank liters kg (density 0.792)
..................................................
Engines supplies 1 5300 4198
2 5770 4570
3 5770 4570
4 5300 4198
Main storages 5 9090 7200
6 14630 11587
7 9350 7405
8 16210 12838
Auxiliary 5A 2810 2225
7A 2810 2225
Transfer and reserve 9 14010 11096
10 15080 11943
11 13150 10415
..................................................
Totals 119280 l 94470 kg
Note that 1 US gal = 3.7854 liters.
Maximum operating altitude : 60000 ft.
Range : 4500 miles (3900 NM).
Speed : max operating Mach 2.04, average takeoff 250 mph (217 kt),
average landing 185 mph (161 kt).
AOA : min -5.5 deg (above Mach 1), max 16.5 deg.
Vortex above the entire wing creates lift at low speed and high AOA.
Ground effect at landing : downwash of the air betweeen the wing and the ground.
Delta wing provides a great deal of lift at Mach speed, with very little drag.
Flight systems (range up and down) : inner elevons 9 deg, middle and
outer elevons 23.5 deg, rudder 30 deg.
Actual travel limits are a little lower than these mechanical limits.
Turbulence mode reduces the trim rate.
Gear :
- main gear : track 7 ft. 72 in., brakes.
- nose : wheelbase to main gear 59 ft. 8 1/4 in., no brake, +/-60 deg steering angle.
- tail : no brake.
- up process takes 12 s : door opening 2 s, gear retract 8 s, door closing 8 s.
Nose :
- from UP : visor transit 0 deg 6-8 s.
- nose transit 5 deg 4-6 s.
- to DOWN : nose transit 12.5 deg 5.7 s.
Max total temperature (TMO) : 127 degC (on nose).
Max oil temperature : start and takeoff 125 degC, takeoff and 5 minutes
transient 195 degC, continuous operation 190 degC,
starting -35 degC, adavance above idle -20 degC.
Mas oil pressure : continued operation 5 PSI, takeoff 10 PSI.
Max fuel temperature : startup -40 degC, advance above idle -40 degC,
continued operation 50 degC.
</documentation>
<documentation>
- http://www.alpa.org/alpa/DesktopModules/ViewDocument.aspx?DocumentID=814 :
Mass gross weight : takeoff lasts 45 s, V1 165 kt, VR 195 kt, V2 220.
Initial pitch at rotation is 13.5 deg.
Cockpit is very noisy until nose is streamlined.
Climb rate is slowly increased from 1500 to 3000 ft/s.
Best lift-over-drag ratio over 300 kt.
At takeoff, center of gravity is 51-52%, 58% at Mach 2.04.
At Mach 1.3, inlet-guide ramps lower to slow down the intake air.
At Mach 1.7 the afterburners are turned off, and the non-bypass engines
are able to increase to Mach 2.04 (1150 kt)
with about half the fuel flow.
At cruise speed, the air entering the engines is reduced by intake
ramps to 500 kt. This drop in intakes provides 45% of thrust, the
engines 50%, and the convergent/divergent effect of the nozzle and
stowed thrust reversers, 5%.
At Mach 2.04, fuel flow is 45200 lb/h.
Heathrow to Kennedy : 3h50.
VREF is 162 kt at 275000 lb.
</documentation>
<documentation>
- http://www.concorde-jet.com/ :
Nose : O deg visor up supersonic, 0 deg visor down subsonic,
5 deg takeoff/subsonic, and 12.5 deg approach/landing/taxi.
Takeoff : 175 kt, in 24 s, 1700-2100 ft/minute.
Landing : 162 kt, 1500-1700 ft/minute.
Subsonic cruise : Mach 0.93.
Fuel : capacity 95680 kg, 20500 kg/h, 10000 at arrival.
Aero reference point steps back of 2 m at Mach 2.
</documentation>
<documentation>
- http://www.club-concorde.org/ :
Min runway : takeoff 3600 m, landing : 2200 m..
Max wing loading : 488 kg/m2.
Max climbing rate : 1525 m/minute.
Takeoff speed : 214 kt.
Landing speed : 130 kt, max 162 kt.
</documentation>
<reference
refID="incident report"
author="BEA"
title="http://www.bea-fr.org/docspa/2000/f-sc000725/htm/f-sc000725.html/"
date="july 2000"/>
<documentation>
Droop nose : 0.53 m.
Front gear from nose (without droop nose) : 18.7 m.
Main gear from front gear : 18.2 m.
Distance of twin engine join : 11 m.
Reheat provides 18% of additional thrust during take off.
TABLE A corresponds to an effective filling at 95% of tanks (94% for tank 5).
It is possible to surpass fuel gauges with 1660 additional liters.
</documentation>
<reference
refID="AIAA Professional studies series"
author="Jean Rech and Clive S. Leyman"
title="A Case Study by Aerospatiale and British Aerospace on the Concorde"
date=""/>
<documentation>
- http://www.aoe.vt.edu/~mason/Mason_f/ConfigAeroSupersonicNotes.pdf/ (Willian H. Mason) :
CG (without CG (with Aerodynamic
Mach fuel transfer) fuel transfer) center location
..............................................................
0.5 53.5 53.5 55.0
0.75 53.5
0.9 55.0 58.0
1.0 55.0 64.5
1.2 63.5
1.5 57.5 62.5
2.0 53.5 58.5 62.0
(all positions in % of aerodynamic chord C0, 90.748 feet).
</documentation>
<documentation>
- http://www.titanic.com/story/159/Concorde/ :
Runway : 11200 ft takeoff, 7300 ft landing.
Max climb rate : 5000 ft/s.
Range : 3550 nm supersonic, 2760 nm subsonic (Mach 0.95 FL300).
Areas (sq ft) : wings (gross) 3856, elevons (total) 344.44, fin
(excluding dorsal fin) 365, rudder 112.
</documentation>
<documentation>
- http://www.dft.gov.uk/stellent/groups/dft_avsafety/documents/page/dft_avsafety_029047.hcsp/
(incident report, 13 june 2003) :
The fuel tanks are arranged in 3 groups : the left main transfer group,
the right main transfer and the trim transfer. The left and right main
transfer groups store fuel in the wings and sections of the center fuselage,
and both groups are comprised of 3 main tanks, which supply 2 collector
tanks per group, from which the engines are fed.
The collector tanks on the right main transfer group are tanks 3 and 4,
which feed engines 3 and 4 respectively. The main fuel transfer system
transfers fuel from the main transfer tanks to the collector tanks at
a rate sufficiently high to ensure that the collectors tanks are always
maintained in a near full condition.
</documentation>
<reference
refID="Nasa TM X-3532"
author="Henry H. Arnaiz"
title="Flight-measured lift and drag characteristics of a large, flexible, high supersonic cruise airplane"
date="May 1977"/>
<documentation>
- http://www.nasa.gov/centers/dryden/pdf/87877main_H-913.pdf :
The lift curve (delta wing) shifts downwards, temporarily at Mach 1.06, and completely near Mach 1.65.
Differences of XB-70 :
- cruise Mach 3 at 70,000 feet.
- wider canards.
- wingtips fold from 0 deg at Mach 0.75 to 65.70 deg at Mach 1.5 (transonic 25.30 deg).
</documentation>
</fileheader>
<metrics>
<documentation>
Pilot's eyepoint location, in aircraft's own coord system, FROM cg.
X, Y, Z, in inches
ORIGIN (0,0,0) is at NOSE.
Center of gravity :
- level at wing level : -1/4 of max external fuselage height (130 in.).
- 51.7%, inside corridor of C0 (maximum takeoff load)
=> real C0 starts over front gear location (18.7 m).
Aero refence point :
- level at wing level : -1/8 of max external fuselage height (130 in.).
- back of center of gravity reduces autopilot roll (step back at supersonic cruise).
It has been found that 200 inches behind CG reduces AUTOPILOT ROLL.
=> real at Mach 2 is 62% of C0.
Eye point location : length from nose to cockpit (24 ft),
1/4 of max external fuselage width (113 in.),
1/4 of max fuselage height (113 in.).
Add ac_wingincidence : 1/20 of wing chord (C0).
Htailarm : distance from CG to horizontal tail tip, none (5 ft).
Vtailarm : distance from CG to vertical tail tip.
</documentation>
<wingarea unit="FT2"> 3856.0000 </wingarea>
<wingspan unit="FT"> 83.8300 </wingspan>
<chord unit="FT"> 90.7500 </chord> <!-- aeromatic 46.0 (C0) -->
<htailarea unit="FT2"> 0.0000 </htailarea> <!-- aeromatic 964.0 -->
<htailarm unit="FT"> 5.0000 </htailarm> <!-- aeromatic 18.0 -->
<vtailarea unit="FT2"> 365.0000 </vtailarea> <!-- aeromatic 771.20 -->
<vtailarm unit="FT"> 5.0000 </vtailarm> <!-- added (turbulence) -->
<wing_incidence unit="DEG"> 2.86 </wing_incidence> <!-- aeromatic none (0.0) -->
<!-- AC_LV 91.05 unit ? -->
<location name="AERORP" unit="IN"> <!-- aeromatic 1335.4, 0.0, 0.0 -->
<x> 736.22 </x>
<y> 0.0000 </y>
<z> -16.2500 </z>
</location>
<location name="EYEPOINT" unit="IN"> <!-- aeromatic 170.0, -32.0, 80.0 -->
<x> 288.0000 </x>
<y> -28.2500 </y>
<z> 32.5000 </z>
</location>
<location name="VRP" unit="IN">
<x> 0.0000 </x>
<y> 0.0000 </y>
<z> 0.0000 </z>
</location>
</metrics>
<mass_balance>
<documentation>
Center of gravity location, empty weight, in aircraft's own structural coord
system. X, Y, Z, in inches; X is positive out the tail, Y positive out the
right wing.
</documentation>
<ixx unit="SLUG*FT2"> 1432000.0000 </ixx> <!-- aeromatic 3419278 -->
<iyy unit="SLUG*FT2"> 19034000.0000 </iyy> <!-- aeromatic 22486091 -->
<izz unit="SLUG*FT2"> 10100000.0000 </izz> <!-- aeromatic 21487661 -->
<ixy unit="SLUG*FT2"> 0.0000 </ixy>
<ixz unit="SLUG*FT2"> 0.0000 </ixz>
<iyz unit="SLUG*FT2"> 0.0000 </iyz>
<emptywt unit="LBS"> 173500.0000 </emptywt> <!-- aeromatic 244800 -->
<location name="CG" unit="IN"> <!-- aeromatic 1335.4, 0.0, -60.7 -->
<x> 1299.4000 </x>
<y> 0.0000 </y>
<z> -32.5000 </z>
</location>
<pointmass name="payload">
<weight unit="LBS"> 29500 </weight>
<location name="payload" unit="IN">
<x> 1299.4 </x>
<y> 0 </y>
<z> -32.5 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<documentation>
- => real nose (18.7 m = 736.2 in.), wing (18.7 m + 18.2 m = 1452.8 in.).
- gear height determined by 3D model, supposed at scale.
- tyre diameter of main gears, at 3/42 of the length between the gears (18.2 m) = 51.2 in.
- adjust the front spring, to be horizontal at full load.
</documentation>
<contact type="BOGEY" name="NOSE_LG">
<location unit="IN">
<x> 736.2000 </x>
<y> 0.0000 </y>
<z> -178.5000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 15000 </damping_coeff>
<max_steer unit="DEG"> 60.0000 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_FWD">
<location unit="IN">
<x> 1427.2000 </x>
<y> -152.0000 </y>
<z> -158.5000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 25000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_REAR">
<location unit="IN">
<x> 1478.4000 </x>
<y> -152.0000 </y>
<z> -158.5000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 25000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_FWD">
<location unit="IN">
<x> 1427.2000 </x>
<y> 152.0000 </y>
<z> -158.5000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 25000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_REAR">
<location unit="IN">
<x> 1478.4000 </x>
<y> 152.0000 </y>
<z> -158.0000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 25000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="TAIL">
<location unit="IN">
<x> 2081.0000 </x>
<y> 0.0000 </y>
<z> 20.0000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000.0000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 25000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<documentation>
additional contact points, for crash detection when gear retracted.
</documentation>
<contact type="STRUCTURE" name="NOSE_TIP">
<location unit="IN">
<x> 0.0000 </x>
<y> 0.0000 </y>
<z> 0.0000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 122400.0000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 40800.0000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="LEFT_TIP">
<location unit="IN">
<x> 1825.2000 </x>
<y> -503.0000 </y>
<z> 0.0000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 122400.0000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 40800.0000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_TIP">
<location unit="IN">
<x> 1825.2000 </x>
<y> 503.0000 </y>
<z> 0.0000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 122400.0000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 40800.0000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="TAIL_TIP">
<location unit="IN">
<x> 2427.6000 </x>
<y> 0.0000 </y>
<z> 50.0000 </z>
</location>
<static_friction> 0.8000 </static_friction>
<dynamic_friction> 0.5000 </dynamic_friction>
<rolling_friction> 0.0200 </rolling_friction>
<spring_coeff unit="LBS/FT"> 122400.0000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 40800.0000 </damping_coeff>
</contact>
</ground_reactions>
<system name="Hydraulics">
<channel name="Nose Wheel Steering">
<scheduled_gain name="systems/hydraulics/nws-pedal-cmd">
<documentation>
default is rudder pedal (flight).
</documentation>
<input>fcs/rudder-cmd-norm</input>
<table>
<independentVar lookup="row">systems/hydraulics/nws-engaged</independentVar>
<tableData>
0 1.0
1 0.0
</tableData>
</table>
<output>fcs/rudder-pedal-norm</output>
</scheduled_gain>
<scheduled_gain name="systems/hydraulics/nws-steer-cmd">
<documentation>
- default is not engaged (flight).
- default is able (hydraulics).
- rudder steering at 10 deg.
</documentation>
<input>fcs/rudder-cmd-norm</input>
<table>
<independentVar lookup="row">systems/hydraulics/nws-engaged</independentVar>
<independentVar lookup="column">systems/hydraulics/nws-unable</independentVar>
<tableData>
0.0 1.0
0 -0.171 -0.0
1 -1.0 -0.0
</tableData>
</table>
<output>fcs/steer-cmd-norm</output>
</scheduled_gain>
</channel>
<channel name="Pitch Hydraulics">
<scheduled_gain name="systems/hydraulics/elevator-yoke-cmd">
<documentation>
default is yoke (flight).
</documentation>
<input>fcs/elevator-cmd-norm</input>
<table>
<independentVar lookup="row">systems/hydraulics/elevon-gravity</independentVar>
<tableData>
0 1.0
1 0.0
</tableData>
</table>
<output>fcs/elevator-yoke-norm</output>
</scheduled_gain>
</channel>
<channel name="Roll Hydraulics">
<scheduled_gain name="systems/hydraulics/aileron-yoke-cmd">
<documentation>
default is yoke (flight).
</documentation>
<input>fcs/aileron-cmd-norm</input>
<table>
<independentVar lookup="row">systems/hydraulics/elevon-gravity</independentVar>
<tableData>
0 1.0
1 0.0
</tableData>
</table>
<output>fcs/aileron-yoke-norm</output>
</scheduled_gain>
</channel>
</system>
<system name="Tractor">
<channel name="Tractor">
<switch name="systems/pushback/linked">
<default value="-1"/>
<test value="0">
/sim/model/pushback/position-norm gt 0.95
/gear/gear/wow == 1
gear/unit[0]/wheel-speed-fps lt 50
</test>
</switch>
<summer name="systems/pushback/speed-error">
<input>/sim/model/pushback/target-speed-fps</input>
<input>-gear/unit[0]/wheel-speed-fps</input>
</summer>
<pid name="systems/pushback/force">
<input>systems/pushback/speed-error</input>
<kp>/sim/model/pushback/kp</kp>
<ki>/sim/model/pushback/ki</ki>
<kd>/sim/model/pushback/kd</kd>
<trigger>systems/pushback/linked</trigger>
<output>/sim/model/pushback/force</output>
</pid>
<switch name="systems/pushback/force-output">
<default value="0"/>
<test value="systems/pushback/force">
systems/pushback/linked == 0
</test>
<output>external_reactions/tractor/magnitude</output>
</switch>
</channel>
</system>
<flight_control name="Concorde">
<property>fcs/elevator-surface</property>
<property>fcs/aileron-surface</property>
<property>fcs/rudder-surface</property>
<channel name="Pitch">
<summer name="Pitch Trim Sum">
<input>fcs/elevator-yoke-norm</input>
<input>fcs/pitch-trim-cmd-norm</input>
<clipto>
<min>-1.0000</min>
<max>1.0000</max>
</clipto>
</summer>
<actuator name="Elevator Actuator">
<input>fcs/pitch-trim-sum</input>
<output>fcs/elevator-surface</output>
</actuator>
<aerosurface_scale name="Elevator Control">
<input>fcs/elevator-surface</input>
<gain>0.0175</gain>
<range>
<documentation>
=> change -0.35/0.30 to -22.5/22.5 deg real.
</documentation>
<min>-22.5000</min>
<max>22.5000</max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Elevator Position Normalizer">
<input>fcs/elevator-surface</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="Roll Trim Sum">
<input>fcs/aileron-yoke-norm</input>
<input>fcs/roll-trim-cmd-norm</input>
<clipto>
<min>-1.0000</min>
<max>1.0000</max>
</clipto>
</summer>
<actuator name="Aileron Actuator">
<input>fcs/roll-trim-sum</input>
<output>fcs/aileron-surface</output>
</actuator>
<aerosurface_scale name="Left Aileron Control">
<input>fcs/aileron-surface</input>
<gain>0.0175</gain>
<range>
<documentation>
=> change 0.35 to 22.5 deg real.
</documentation>
<min>-22.5000</min>
<max>22.5000</max>
</range>
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Left Aileron Position Normalizer">
<input>fcs/aileron-surface</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Control">
<input>-fcs/aileron-surface</input>
<gain>0.0175</gain>
<range>
<documentation>
=> change 0.35 to 22.5 deg real.
</documentation>
<min>-22.5000</min>
<max>22.5000</max>
</range>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Position Normalizer">
<input>fcs/aileron-surface</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/right-aileron-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Yaw">
<summer name="Rudder Command Sum">
<input>fcs/rudder-pedal-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min>-1.0000</min>
<max>1.0000</max>
</clipto>
</summer>
<scheduled_gain name="Yaw Damper Rate">
<input>velocities/r-aero-rad_sec</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
3.0000 0.0000
11.0000 2.0000
</tableData>
</table>
</scheduled_gain>
<scheduled_gain name="Yaw Damper Beta">
<input>aero/beta-rad</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
3.0000 0.0000
11.0000 0.0000
</tableData>
</table>
</scheduled_gain>
<summer name="Yaw Damper Sum">
<input>fcs/yaw-damper-beta</input>
<input>fcs/yaw-damper-rate</input>
<clipto>
<min>-0.2000</min>
<max>0.2000</max>
</clipto>
</summer>
<scheduled_gain name="Yaw Damper Final">
<input>fcs/yaw-damper-sum</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
2.9900 0.0000
3.0000 1.0000
</tableData>
</table>
</scheduled_gain>
<summer name="Rudder Sum">
<input>fcs/rudder-command-sum</input>
<input>fcs/yaw-damper-final</input>
<clipto>
<min>-1.0000</min>
<max>1.0000</max>
</clipto>
</summer>
<actuator name="Rudder Actuator">
<input>fcs/rudder-sum</input>
<output>fcs/rudder-surface</output>
</actuator>
<aerosurface_scale name="Rudder Control">
<input>fcs/rudder-surface</input>
<gain>0.0175</gain>
<range>
<documentation>
=> change 0.35 to 29 deg real.
</documentation>
<min>-29.0000</min>
<max>29.0000</max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Rudder Position Normalizer">
<input>fcs/rudder-surface</input>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/rudder-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Aeromechanical">
<kinematic name="Flaps Control">
<input>fcs/flap-cmd-norm</input>
<traverse>
<documentation>
changed 30 deg / 3 positions : use flaps as nose.
</documentation>
<setting>
<position>0.0000</position>
<time>0.0000</time>
</setting>
<setting>
<position>0.0000</position>
<time>7.0000</time>
</setting>
<setting>
<position>5.0000</position>
<time>5.0000</time>
</setting>
<setting>
<position>12.5000</position>
<time>6.0000</time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="Flap Position Normalizer">
<input>fcs/flap-pos-deg</input>
<domain>
<min>0</min>
<max>12.5</max>
</domain>
<range>
<min>0</min>
<max>1</max>
</range>
<output>fcs/flap-pos-norm</output>
</aerosurface_scale>
<kinematic name="Gear Control">
<input>gear/gear-cmd-norm</input>
<traverse>
<documentation>
=> up in 12 s.
</documentation>
<setting>
<position>0.0000</position>
<time>0.0000</time>
</setting>
<setting>
<position>1.0000</position>
<time>12.0000</time>
</setting>
</traverse>
<output>gear/gear-pos-norm</output>
</kinematic>
<kinematic name="Speedbrake Control">
<input>fcs/speedbrake-cmd-norm</input>
<traverse>
<setting>
<position>0.0000</position>
<time>0.0000</time>
</setting>
<setting>
<position>1.0000</position>
<time>1.0000</time>
</setting>
</traverse>
<output>fcs/speedbrake-pos-norm</output>
</kinematic>
</channel>
</flight_control>
<propulsion>
<documentation>
- after FCS, which creates the intake command variable.
- air intake on (supersonic) by default.
</documentation>
<documentation>
- Engine center at 5/7 of length (2428 in.), -2/5 of fuselage height (130 in.).
- Border aligned with main gear track (304 in. / 2).
=> real engine diameter is 1.65 m = (11 - 7.7) / 2.
- Thruster center 3/4 of length (2428 in.), aligned with engines.
</documentation>
<engine file="Olympus593Mrk610">
<location unit="IN">
<x> 1734.0000 </x>
<y> -249.4000 </y>
<z> -52.0000 </z> <!-- aeromatic -40 -->
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0000 </pitch>