jsbsim.js

<?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> 14 August 2010 </filecreationdate> <version> 1.13 </version> <description>Aerospatiale/British Aerospace Concorde</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> <note> This model was created using publicly available data, publicly available technical reports, textbooks, and guesses. It contains no proprietary or restricted data. If this model has been validated at all, it would be only to the extent that it seems to "fly right", and that it possibly complies with published, publicly known, performance data (maximum speed, endurance, etc.). Thus, this model is meant for educational and entertainment purposes only. This simulation model is not endorsed by the manufacturer. This model is not to be sold. </note>  <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>  <htailarea unit="FT2"> 0.0000 </htailarea>  <htailarm unit="FT"> 5.0000 </htailarm>  <vtailarea unit="FT2"> 365.0000 </vtailarea>  <vtailarm unit="FT"> 5.0000 </vtailarm>  <wing_incidence unit="DEG"> 2.86 </wing_incidence>   <location name="AERORP" unit="IN">  <x> 736.22 </x> <y> 0.0000 </y> <z> -16.2500 </z> </location> <location name="EYEPOINT" unit="IN">  <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>  <iyy unit="SLUG*FT2"> 19034000.0000 </iyy>  <izz unit="SLUG*FT2"> 10100000.0000 </izz>  <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>  <location name="CG" unit="IN">  <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"> 40000.0000 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 40800.0000 </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"> 408000.0000 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 81600.0000 </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"> 408000.0000 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 81600.0000 </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"> 408000.0000 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 81600.0000 </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"> 408000.0000 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 81600.0000 </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"> 122400.0000 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 40800.0000 </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="Nose Wheel Steering"> <property>systems/NWS/engaged</property> <property value="1">systems/NWS/hydraulics</property> <channel name="Nose Wheel Steering"> <scheduled_gain name="systems/NWS/pedal-cmd"> <documentation> default is rudder pedal (flight). </documentation> <input>fcs/rudder-cmd-norm</input> <table> <independentVar lookup="row">systems/NWS/engaged</independentVar> <tableData> 0 1.0 1 0.0 </tableData> </table> <output>fcs/rudder-pedal-norm</output> </scheduled_gain> <scheduled_gain name="systems/NWS/steer-cmd"> <documentation> - default is no wheel steering (flight). - default is hydraulics. - rudder steering at 10 deg. </documentation> <input>fcs/rudder-cmd-norm</input> <table> <independentVar lookup="row">systems/NWS/engaged</independentVar> <independentVar lookup="column">systems/NWS/hydraulics</independentVar> <tableData> 0.0 1.0 0 -0.0 -0.171 1 -0.0 -1.0 </tableData> </table> <output>fcs/steer-cmd-norm</output> </scheduled_gain> </channel> </system> <system name="Tractor"> <property>/sim/model/pushback/target-speed-fps</property> <property>/sim/model/pushback/position-norm</property> <channel name="Tractor"> <switch name="systems/pushback/linked"> <default value="-1"/> <test value="0"> /sim/model/pushback/position-norm gt 0.95 gear/unit[0]/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-cmd-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-cmd-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> <property>fcs/ground-idle</property> <property>fcs/intake-subsonic-pos</property> <engine file="Olympus593Mrk610"> <location unit="IN"> <x> 1734.0000 </x> <y> -249.4000 </y> <z> -52.0000 </z>  </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0.0000 </pitch> <yaw> 0.0000 </yaw> </orient> <feed>13</feed> <thruster file="direct"> <location unit="IN"> <x> 1821.0000 </x> <y> -249.4000 </y> <z> -52.0000 </z> </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0.0 </pitch> <yaw> 0.0 </yaw> </orient> </thruster> </engine> <engine file="Olympus593Mrk610"> <location unit="IN"> <x> 1734.0000 </x> <y> -184.5000 </y> <z> -52.0000 </z> </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0.0000 </pitch> <yaw> 0.0000 </yaw> </orient> <feed>14</feed> <thruster file="direct"> <location unit="IN"> <x> 1821.0000 </x> <y> -184.5000 </y> <z> -52.0000 </z> </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0.0 </pitch> <yaw> 0.0 </yaw> </orient> </thruster> </engine> <engine file="Olympus593Mrk610"> <location unit="IN"> <x> 1734.0000 </x> <y> 184.5000 </y> <z> -52.0000 </z> </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0.0000 </pitch> <yaw> 0.0000 </yaw> </orient> <feed>15</feed> <thruster file="direct"> <location unit="IN"> <x> 1821.0000 </x> <y> 184.5000 </y> <z> -52.0000 </z> </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0.0 </pitch> <yaw> 0.0 </yaw> </orient> </thruster> </engine> <engine file="Olympus593Mrk610"> <location unit="IN"> <x> 1734.0000 </x> <y> 249.4000 </y> <z> -52.0000 </z> </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0.0000 </pitch> <yaw> 0.0000 </yaw> </orient> <feed>16</feed> <thruster file="direct"> <location unit="IN"> <x> 1821.0000 </x> <y> 249.4000 </y> <z> -52.0000 </z> </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0.0 </pitch> <yaw> 0.0 </yaw> </orient> </thruster> </engine> <documentation> The parameters are gear track, and tank 5 radius; to check against engine center. => Real length is arm, % of MAC (see table above) : real MAC (C0 1089 in.) starts at 18.7 m (736.2 in.). => Real half gear track is 7.7 m / 2 (151.6 in.). Configuration for take off with maximum weight : all tanks full, except tank 11 at 86%. </documentation> <tank type="FUEL">  <documentation> Tank 1 : - 1/2 radius of tank 5. - align 3/4 of gear track. - => 39.80 % MAC. </documentation> <location unit="IN"> <x> 1170.0000 </x> <y> -114.0000 </y> <z> -12.0000 </z>  </location> <radius unit="IN"> 50 </radius> <capacity unit="LBS"> 9255.0100 </capacity> <contents unit="LBS"> 9255.0100 </contents> <temperature> 59 </temperature>  </tank> <tank type="FUEL">  <documentation> Tank 2 : - 1/2 radius of tank 5. - align 1/2 of gear track. - near engine center. - => 76.10 % MAC. </documentation> <location unit="IN"> <x> 1565.0000 </x> <y> -76.0000 </y> <z> -12.0000 </z> </location> <radius unit="IN"> 50 </radius> <capacity unit="LBS"> 10075.1300 </capacity> <contents unit="LBS"> 10075.1300 </contents> <temperature> 59 </temperature> </tank> <tank type="FUEL">  <documentation> Tank 3 : - 1/2 radius of tank 5. - align 1/2 of gear track. - near engine center. - => 76.10 % MAC. </documentation> <location unit="IN"> <x> 1565.0000 </x> <y> 76.0000 </y> <z> -12.0000 </z> </location> <radius unit="IN"> 50 </radius> <capacity unit="LBS"> 10075.1300 </capacity> <contents unit="LBS"> 10075.1300 </contents> <temperature> 59 </temperature> </tank> <tank type="FUEL">  <documentation> Tank 4 : - 1/2 radius of tank 5. - align 3/4 of gear track. - => 39.80 % MAC </documentation> <location unit="IN"> <x> 1170.0000 </x> <y> 114.0000 </y> <z> -12.0000 </z> </location> <radius unit="IN"> 50 </radius> <capacity unit="LBS"> 9255.0100 </capacity> <contents unit="LBS"> 9255.0100 </contents> <temperature> 59 </temperature> </tank> <tank type="FUEL">  <documentation> Tank 5 : - center + radius = gear position. - => 49.40 % MAC. </documentation> <location unit="IN"> <x> 1274.0000 </x> <y> -152.0000 </y> <z> -12.0000 </z> </location> <radius unit="IN"> 100 </radius> <capacity unit="LBS"> 15873.2800 </capacity> <contents unit="LBS"> 15873.2800 </contents> </tank> <tank type="FUEL">  <documentation> Tank 6 : - 3/2 radius of tank 5. - align 1/2 of gear track. - before engine center. - => 66.70 % MAC. </documentation> <location unit="IN"> <x> 1463.0000 </x> <y> -76.0000 </y> <z> -12.0000 </z> </location> <radius unit="IN"> 150 </radius> <capacity unit="LBS"> 25544.9600 </capacity> <contents unit="LBS"> 25544.9600 </contents> </tank> <tank type="FUEL">  <documentation> Tank 7 : - radius of tank 5. - before engine center. - => 64.70 % MAC. </documentation> <location unit="IN"> <x> 1441.0000 </x> <y> 152.0000 </y> <z> -12.0000 </z> </location> <radius unit="IN"> 100 </radius> <capacity unit="LBS"> 16325.2300 </capacity> <contents unit="LBS"> 16325.2300 </contents> </tank> <tank type="FUEL">  <documentation> Tank 8 : - 3/2 radius of tank 5. - align 1/2 of gear track. - => 46.70 % MAC. </documentation> <location unit="IN"> <x> 1245.0000 </x> <y> 76.0000 </y> <z> -12.0000 </z> </location> <radius unit="IN"> 150 </radius> <capacity unit="LBS"> 28302.9500 </capacity> <contents unit="LBS"> 28302.9500 </contents> </tank> <tank type="FUEL">  <documentation> Tank 9 : - 3/2 radius of tank 5. - centred on plane axis. - => 16.90 % MAC </documentation> <location unit="IN"> <x> 920.0000 </x> <y> 0.0000 </y> <z> -12.0000 </z> </location> <radius unit="IN"> 150 </radius> <capacity unit="LBS"> 24462.4900 </capacity> <contents unit="LBS"> 24462.4900 </contents> </tank> <tank type="FUEL">  <documentation> Tank 10 : - 1/2 radius of tank 5. - centered on plane axis.