shuttle.xml

<?xml version="1.0" encoding="UTF-8"?>

<!--###################################################################################
    Antonov-Aircrafts and SpaceShuttle :: Herbert Wagner November2014-March2015
    Development is ongoing, see latest version: www.github.com/herbyw/antonov-aircrafts
    This file is licenced under the terms of the GNU General Public Licence V3 or later
    
    Firefly: 3D model improvment: ruder, speedbreak, ailerions, all gears and doors
    
    ###################################################################################
-->

<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="shuttle" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author>HerbyW</author>
  <filecreationdate>03-2015</filecreationdate>
  <version>$Revison: 5$</version>
  <description>Space Shuttle Model JSBSim</description>
 </fileheader>

<!--
  File:     shuttle.xml
  Inputs:
    name:          shuttle
    type:          three-engine transonic transport
    max weight:    240000 lb                   82499 kg
    wing span:     78.06 ft                    23.79 m    ok
    length:        122.17 ft                  37.237 m    ok
    wing area:     2691.25 sq-ft              250 qm      ok
    gear type:     tricycle
    retractable?:  yes
    # engines:     3
    engine type:   rocket
    engine layout: aft fuselage
    yaw damper?    yes
  Outputs:
    wing loading:  89.18 lb/sq-ft
    CL-alpha:      4.4 per radian
    CL-0:          0.2
    CL-max:        1.2
    CD-0:          0.019
    K:             0.042
 
 http://www.bernd-leitenberger.de/shuttle-mission.shtml
 
Gesamtsystem:

Startmasse 1.992.500 kg                        4.392.710 lb  ok

Orbiter:

Maximale Startmasse: 110900 kg                    244492 lb  ok
maximale Nutzlast: 29500 kg                        65036 lb  ok
maximale zurückgeführte Nutzlast: 14500 kg         31967 lb
Landemasse leer: 70800 kg                         156087 lb
Trockengewicht 68060 kg                           150046 lb
Höhe: 16.4 m
Länge: 37.2 m
Spannweite: 23.8 m
Flügelfläche: 250 m²

Subsysteme:

Struktur: 22450 kg                                  49493 lb
Haupttriebwerke und Schubgerüst: 12000 kg           26455 lb
Wärmeschutz: 11400 kg                               25132 lb
OMS und RCS Treibstoffe: 9370 kg                    20657 lb
Lande- und Dockeinrichtungen: 4300 kg                9480 lb
Elektrische Stromversorgung: 3670 kg                 8090 lb
Hilfstriebwerke: 2370 kg                             5225 lb
Hydraulik: 2370 kg                                   5225 lb
Elektronikausrüstung: 2050 kg                        4519 lb
Klimaausrüstung / Lebenserhaltung: 1940 kg
Verlustmassen (Gase, Abwasser, Sprengvorrichtungen): 1800 kg
Flüssigkeiten + Resttreibstoffe: 1620 kg
Steuerruder: 835 kg
Ausrüstung für Besatzung: 630 kg
Besatzung: 550 kg
Reserve: 5700 kg                                     12566 lb

Besatzung 3-7 (Notfälle 10)
Missionsdauer nominal: 7 Tage
Mit zusätzlicher Ausrüstung maximal: 30 Tage

Triebwerke

3 x SSME:

Triebstoffe: LOX / LH2
Schub Boden 1668 kN
Schub Vakuum: 2090 kN Nominell, 2270 kN (109 %)
Regelbereich: 50-109 %
Länge: 4.3 m
Gewicht: 2880 kg                                   6349 lb
Spezifischer Impuls Vakuum: 4462 m/s
Spezifischer Impuls Boden: 3560 m/s
Brennzeit: 480 Sekunden
Lebensdauer: maximal 55 Flüge
Brennkammerdruck: 200 Bar

2 x OMS

Treibstoffe: NTO / MMH
Schub: 26.7 kN
max. Geschwindigkeitsänderung: 305 m/s
je weiterer Zusatztank: 152 m/s
spezifischer Impuls: 3020 m/s.

38 x RCS

Treibstoffe: NTO / MMH
Schub: 3.87 kN

Energieversorgung

3 Brennstoffzellen mit je 7 kW Nennleistung (maximal 10 kW)
3 Hilfsgeneratoren mit katalytischer Hydrazinzersetzung / Turbine je 5 kW Leistung
3 Nickelcadmiumbatterien von je 10 Ah
Hydrauliksystem: 4 Hydrazin Turbinen mit je 150 PS Leistung

Externer Tank

Höhe: 46,85 m
Durchmesser: 8,38 m                                              ok
Startmasse: 734200 kg                              1618634 lb    ok
Leermasse: 31300 kg                                  69004 lb
Tankvolumen LOX: 552 m³
Tankvolumen LH2: 1535 m³

Feststoffbooster

Länge: 45,4 m
Durchmesser: 3,71 m                                            ok
Startmasse: 573700 kg                              1264792 lb  ok
Leermasse: 82500 kg                                 181881 lb
Schub am Boden: 11830 kN
spezifischer Impuls (Durchschnitt): 2538 m/s
Brennzeit: 120 sec

Gesamtmasse: 111+734+573+573= 1.990 t

Cockpit wiew:
http://www.businessinsider.com/breathtaking-images-of-the-space-shuttle-2013-9?IR=T

-->

 <metrics>
   <wingarea  unit="FT2"> 2691.25 </wingarea>
   <wingspan  unit="FT" >   78.06 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   34.48 </chord>
   <htailarea unit="FT2">  672.81 </htailarea>
   <htailarm  unit="FT" >   54.98 </htailarm>
   <vtailarea unit="FT2">  538.25 </vtailarea>
   <vtailarm  unit="FT" >   54.98 </vtailarm>
   <location name="AERORP" unit="M">
     <x>   2.70 </x>
     <y>   0.00 </y>
     <z>  -2.70 </z>
   </location>
   <location name="EYEPOINT" unit="M">
     <x> 102.62 </x>
     <y> -30.00 </y>
     <z>  75.00 </z>
   </location>
   <location name="VRP" unit="M">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <!--changing some values: ixx from  425779 to 2025779
                           izz from 2475373 to 4575373
                        emtywt from  172000 to  180000
                    location z from     1.0 to     5.0-->
 <mass_balance>
   <ixx unit="SLUG*FT2">   3025779 </ixx>
   <iyy unit="SLUG*FT2">   5162623 </iyy>
   <izz unit="SLUG*FT2">   5575373 </izz>
   <emptywt unit="LBS" >    180000 </emptywt>
   <location name="CG" unit="M">
     <x>   2.70 </x>
     <y>   0.00 </y>
     <z>  -2.70 </z>
   </location>
        <pointmass name="Equipment">
            <weight unit="LBS"> 40000 </weight>
            <location name="POINTMASS" unit="M">
                <x>  2.7 </x>
                <y>  0.0 </y>
                <z> -2.7 </z>
            </location>
        </pointmass>
 </mass_balance>

 <ground_reactions>

<contact type="BOGEY" name="NOSE">
<location unit="M">
<x> -15.00 </x>
<y> 0.00 </y>
<z> -7.18 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.20 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 55000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 11000.00 </damping_coeff>
<max_steer unit="DEG"> 20.00 </max_steer>
<brake_group>NONE</brake_group>
<retractable>1</retractable>
</contact>

<contact type="BOGEY" name="LEFT_MAIN">
<location unit="M">
<x> 3.60 </x>
<y> -4.2 </y>
<z>-7.92 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.20 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 1750000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 110000.00 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>LEFT</brake_group>
<retractable>1</retractable>
</contact>

<contact type="BOGEY" name="RIGHT_MAIN">
<location unit="M">
<x> 3.60 </x>
<y> 4.2 </y>
<z>-7.92 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.20 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 1750000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 110000.00 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>RIGHT</brake_group>
<retractable>1</retractable>
</contact>

  <contact type="STRUCTURE" name="FRONT_LEG">
   <location unit="IN">
     <x> 300.00 </x>
     <y> 300.00 </y>
     <z> 400.00 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      412500.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 82500.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="FRONT2_LEG">
   <location unit="IN">
     <x> 300.00 </x>
     <y>-300.00 </y>
     <z> 400.00 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      412500.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 82500.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="LEFT_LEG">
   <location unit="IN">
     <x> 300.00 </x>
     <y>-300.00 </y>
     <z> -80.00 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      412500.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 82500.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_LEG">
   <location unit="IN">
     <x> 300.00 </x>
     <y> 300.00 </y>
     <z> -80.00 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      412500.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 82500.00 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>
   <!--3 Shuttle Engines reduced to one engine n=0 -->
   <engine file="XLR99">
    <location unit="IN">
      <x> 200.00 </x>
      <y>   0.00 </y>
      <z>   0.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
                             <feed>0</feed>    
    <thruster file="xlr99_nozzle">
     <location unit="IN">
      <x> 200.00 </x>
      <y>   0.00 </y>
      <z>   0.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>   

<!--2 Booster Engines redused to one engine n=1 -->
   <engine file="SRB">
    <location unit="IN">
      <x> 200.00 </x>
      <y>  0.00 </y>
      <z>-241.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>    
                               <feed>1</feed>
    
    <thruster file="SRB_nozzle">
     <location unit="IN">
      <x> 200.00 </x>
      <y>  0.00 </y>
      <z>-241.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>
  

<!--OMS-main engine on right Tail position n=2, red lights iluminate Position and funktion-->

   <engine file="OMS-maintest">
    <location unit="M">
      <x> 12.95 </x>
       <y> 2.00 </y>
       <z> -1.5 </z>
    </location>
    <orient unit="DEG">
      <pitch> 4.0 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>    
                                 <feed>2</feed>    
    <thruster file="OMS-maintest-Nozzle">
     <location unit="M">
      <x> 12.95 </x>
       <y> 2.00 </y>
       <z> -1.5 </z>
    </location>
     <orient unit="DEG">
       <pitch> 4.0 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
    </engine>
    
 <!--extra engines for outer space control Wing Leveler Controls up+down l+r n=3,4 -->
    <engine file="XLR01">
    <location unit="M">
      <x>9.45</x>
      <y>-11.4</y>
      <z>-4.46</z>
    </location>
    <orient unit="DEG">
      <pitch>-90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
                        <feed>3</feed>
			<feed>4</feed>    
    <thruster file="xlr01_nozzle">     
      <location unit="M">
      <x>9.45</x>
      <y>-11.4</y>
      <z>-4.46</z>
      </location>
     <orient unit="DEG">
       <pitch>-90.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>    0.00 </yaw>
     </orient>
    </thruster>
  </engine>
  
  <engine file="XLR01">
    <location unit="M">
      <x>9.45</x>
      <y>11.4</y>
      <z>-4.46</z>
    </location>
    <orient unit="DEG">
      <pitch>-90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
                        <feed>3</feed>
			<feed>4</feed>    
    <thruster file="xlr01_nozzle">     
      <location unit="M">
      <x>9.45</x>
      <y>11.4</y>
      <z>-4.46</z>
      </location>
     <orient unit="DEG">
       <pitch>-90.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>    0.00 </yaw>
     </orient>
    </thruster>
  </engine>
   
<!--OMS-main engine on Tail left position n=5 -->

   <engine file="OMS-maintest">
    <location unit="M">
      <x> 12.95 </x>
       <y> -2.00 </y>
       <z> -1.5 </z>
    </location>
    <orient unit="DEG">
      <pitch> 4.0 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>    
                                 <feed>2</feed>    
    <thruster file="OMS-maintest-Nozzle">
     <location unit="M">
      <x> 12.95 </x>
       <y> -2.00 </y>
       <z> -1.5 </z>
    </location>
     <orient unit="DEG">
       <pitch> 4.0 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
    </engine>
    
 <!--extra engine for outer space control Pitch Leveler Controls
    on nose position n=6 smoke is still as it would be 4 engines-->
    
  <engine file="XLR01">
    <location unit="M">
      <x>-17.50 </x>
      <y>   0.0 </y>
      <z> -2.30 </z>
    </location>
    <orient unit="DEG">
      <pitch> -90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
                        <feed>3</feed>
			<feed>4</feed>    
    <thruster file="xlr01_nozzle">     
      <location unit="M">
      <x>-17.50 </x>
      <y>   0.0 </y>
      <z> -2.30 </z>
      </location>
     <orient unit="DEG">
       <pitch> -90.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>    0.00 </yaw>
     </orient>
    </thruster>    
  </engine>  
  
  <!--7/8 extra engines for outer space control Wing Leveler Controls down l+r-->
    
    <!--free -->
    <!--free -->
    <!--free -->
    <engine file="XLR01x">
    <location unit="M">
      <x>9.45</x>
      <y>0.0</y>
      <z>-4.46</z>
    </location>
    <orient unit="DEG">
      <pitch> 90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
                        <feed>3</feed>
			<feed>4</feed>
			
    <thruster file="xlr01x_nozzle">     
      <location unit="M">
      <x>9.45</x>
      <y>0.0</y>
      <z>-4.46</z>
      </location>
     <orient unit="DEG">
       <pitch> 90.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>
  
  <!--free -->
  <!--free -->
  <!--free -->
  
  <engine file="XLR01x">
    <location unit="M">
      <x>9.45</x>
      <y>0.0</y>
      <z>-4.46</z>
    </location>
    <orient unit="DEG">
      <pitch> 90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
                        <feed>3</feed>
			<feed>4</feed>
			
    
    <thruster file="xlr01x_nozzle">    
      <location unit="M">
      <x>9.45</x>
      <y>0.0</y>
      <z>-4.46</z>
      </location>
     <orient unit="DEG">
       <pitch> 90.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>
  
<!--extra engine for outer space control Pitch Leveler Controls
    on tail position n=9 is not used, n=10 smoke is still as 4 engines-->
    
    <!--free -->
    <!--free -->
    <!--free -->
  
    <engine file="XLR01x">
    <location unit="M">
      <x> 13.00 </x>
      <y>  0.0  </y>
      <z> -5.30 </z>
    </location>
    <orient unit="DEG">
      <pitch> 90.00 </pitch>
      <roll>    0.00 </roll>
      <yaw>     0.00 </yaw>
    </orient>
                        <feed>3</feed>
			<feed>4</feed>
			
    
    <thruster file="xlr01x_nozzle">     
      <location unit="M">
      <x> 13.00 </x>
      <y>  0.0  </y>
      <z> -5.30 </z>
      </location>
     <orient unit="DEG">
       <pitch> 90.00 </pitch>
       <roll>    0.00 </roll>
       <yaw>     0.00 </yaw>
     </orient>
    </thruster>
  </engine>
  
  <engine file="XLR01">
    <location unit="M">
      <x> 13.00 </x>
      <y>  0.0 </y>
      <z>  0.70 </z>
    </location>
    <orient unit="DEG">
      <pitch> -90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
                        <feed>3</feed>
			<feed>4</feed>
			
    
    <thruster file="xlr01_nozzle">     
      <location unit="M">
      <x> 13.00 </x>
      <y>  0.0 </y>
      <z>  0.70 </z>
      </location>
     <orient unit="DEG">
       <pitch> -90.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>    0.00 </yaw>
     </orient>
    </thruster>
  </engine>
  
  <!--extra engine for outer space Yaw Control
    on nose position n=11 smoke is still as 2 engines -->

    <engine file="XLR01">
    <location unit="M">
      <x> -18.95 </x>
      <y>  0.0  </y>
      <z> -3.75 </z>
    </location>
    <orient unit="DEG">
      <pitch>   180.00 </pitch>
      <roll>    90.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
                        <feed>3</feed>
			<feed>4</feed>
			
    
    <thruster file="xlr01_nozzle">     
      <location unit="M">
      <x> -18.95 </x>
      <y>  0.0  </y>
      <z> -3.75 </z>
      </location>
     <orient unit="DEG">
       <pitch>   180.00 </pitch>
       <roll>    90.00 </roll>
       <yaw>    0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  
<!--tank definitions -->
  <tank type="FUEL" number="0">
     <location unit="IN">
       <x> 1.00 </x>
       <y>   0.00 </y>
       <z>-241.00 </z>
     </location>
     <capacity unit="LBS"> 1618634.00 </capacity>
     <contents unit="LBS"> 300000.00 </contents>
     <priority>1</priority>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> 1.00 </x>
       <y>   0.00 </y>
       <z>-241.00 </z>
     </location>
     <capacity unit="LBS"> 2529650.00 </capacity>
     <contents unit="LBS"> 200000.00 </contents>
  </tank>
 
 <!--new tank for manouver engines -->
 
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x> 1.00 </x>
       <y>   0.00 </y>
       <z>-100.00 </z>
     </location>
     <capacity unit="LBS"> 27265.00 </capacity>
     <contents unit="LBS"> 10.0 </contents>
     <priority>2</priority>
  </tank>
 
 <!--new tanks for control engines  beginn-->
 
                <tank type="OXIDIZER" number="3">
			<location unit="IN">
				<x> 0.0 </x>
				<y> 0.0 </y>
				<z> -4.251 </z>
			</location>
			<capacity unit="LBS"> 13500.00 </capacity>
		<!--	<contents unit="LBS"> 4828.00 </contents> -->
			<contents unit="LBS"> 0.10 </contents>
			<density unit="KG/L"> 1.14 </density>
		</tank>

		<tank type="FUEL" number="4">
			<location unit="IN">
				<x> 0.0 </x>
				<y> 0.0 </y>
				<z> -4.251 </z>
			</location>
			<capacity unit="LBS"> 6500.00 </capacity>
		<!--	<contents unit="LBS"> 2204.00 </contents> -->
			<contents unit="LBS"> 0.10 </contents>
			<density unit="LBS/GAL"> 6.88 </density>
		</tank>
 
<!--new tanks for control engines  end-->
 
 </propulsion>

 <flight_control name="FCS: shuttle">

  <channel name="Pitch">
   <summer name="Pitch Trim Sum">
      <input>fcs/elevator-cmd-norm</input>
      <input>fcs/pitch-trim-cmd-norm</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Elevator Control">
      <input>fcs/pitch-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <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 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Left Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/left-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="left aileron normalization">
      <input>fcs/left-aileron-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/left-aileron-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="right aileron normalization">
      <input>fcs/right-aileron-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <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-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </clipto>
   </summer>

   <scheduled_gain name="Yaw Damper Rate">
      <input>velocities/r-aero-rad_sec</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
         <tableData>
            30     0.00
            60     2.00
         </tableData>
      </table>
   </scheduled_gain>

   <scheduled_gain name="Yaw Damper Beta">
      <input>aero/beta-rad</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           30     0.00
           60     0.00
        </tableData>
      </table>
   </scheduled_gain>

   <summer name="Yaw Damper Sum">
      <input>fcs/yaw-damper-beta</input>
      <input>fcs/yaw-damper-rate</input>
      <clipto>
        <min> -0.1 </min>
        <max>  0.1 </max>
      </clipto>
   </summer>

   <scheduled_gain name="Yaw Damper Final">
      <input>fcs/yaw-damper-sum</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           30         0.0
           31         1.0
        </tableData>
      </table>
   </scheduled_gain>

   <summer name="Rudder Sum">
      <input>fcs/rudder-command-sum</input>
      <input>fcs/yaw-damper-final</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Flaps">
   <kinematic name="Flaps Control">
     <input>fcs/flap-cmd-norm</input>
     <traverse>
       <setting>
          <position>  0 </position>
          <time>      0 </time>
       </setting>
       <setting>
          <position>  4 </position>
          <time>      4 </time>
       </setting>
       <setting>
          <position> 8 </position>
          <time>     3 </time>
       </setting>
       <setting>
          <position> 12 </position>
          <time>      3 </time>
       </setting>
     </traverse>
     <output>fcs/flap-pos-deg</output>
   </kinematic>

   <aerosurface_scale name="flap normalization">
      <input>fcs/flap-pos-deg</input>
      <domain>
        <min>  0 </min>
        <max> 12 </max>
      </domain>
      <range>
        <min> 0 </min>
        <max> 1 </max>
      </range>
      <output>fcs/flap-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Landing Gear">
   <kinematic name="Gear Control">
     <input>gear/gear-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     5 </time>
       </setting>
     </traverse>
     <output>gear/gear-pos-norm</output>
   </kinematic>

  </channel>

  <channel name="Speedbrake">
   <kinematic name="Speedbrake Control">
     <input>fcs/speedbrake-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     3 </time>
       </setting>
     </traverse>
     <output>fcs/speedbrake-pos-norm</output>
   </kinematic>

  </channel>
 
 
 <!-- Parachute -->
  <channel name="chute">
   <fcs_function name="fcs/parachute_reef_pos_norm">
    <function>
     <sum>
      <property>/controls/shuttle/parachute</property>      
     </sum>
    </function>
    <clipto>
     <min>0.0</min>
     <max>1.0</max>
    </clipto>
   </fcs_function>
  <pure_gain name="metrics/Schute-sqft">
    <input>fcs/parachute_reef_pos_norm</input>
    <gain> 600.0 </gain> <!-- Area of braking chute = ca 650-->
   </pure_gain>
  </channel>
<!-- Parachute -->
  
  

 </flight_control>

 <aerodynamics>

  <axis name="LIFT">

    <function name="aero/coefficient/CLalpha">
      <description>Lift_due_to_alpha</description>
      <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
			<independentVar lookup="row">aero/alpha-rad</independentVar>
			<independentVar lookup="column">velocities/mach</independentVar>
			<tableData> 
	 0.30	 0.40	 0.50	 0.90
-0.79	-2.69	-2.66	-2.61	-2.54
-0.61	-2.64	-2.62	-2.59	-2.52
-0.52	-2.45	-2.43	-2.39	-2.33
-0.35	-1.74	-1.74	-1.74	-1.69
-0.18	-0.84	-0.85	-0.85	-0.83
 0.00	 0.00	 0.00	 0.00	 0.00
 0.18	 0.89	 0.90	 0.90	 0.88
 0.35	 2.11	 2.11	 2.11	 2.05
 0.52	 3.33	 3.31	 3.28	 3.19
 0.61	 3.68	 3.62	 3.53	 3.44
 0.79	 3.17	 3.22	 3.28	 3.19
			</tableData>
		</table>
	</product> <!--  0.20 -0.680, 0.00 0.200, 0.23 1.200, 0.60 0.600  -->
    </function>

    <function name="aero/coefficient/dCLflap">
       <description>Delta_Lift_due_to_flaps</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <table>
                  <independentVar>fcs/flap-pos-deg</independentVar>
                  <tableData>
                      0.0000	0.000	
                      4.0000	0.001	
                      8.0000	0.002	
                     12.0000	0.003                     
                  </tableData>
              </table>
       </product>
    </function>

    <function name="aero/coefficient/dCLsb">
       <description>Delta_Lift_due_to_speedbrake</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>-0.25</value>
       </product>
    </function>
      
    <function name="aero/coefficient/CLde">
       <description>Lift_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-rad</property>
           <value>0.2</value>
       </product>
    </function>

    <!-- Parachute -1.4 war -0.4-->
    <function name="aero/coefficient/dClpc">
    <description>Delta_Lift_due_to_chute</description>
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Schute-sqft</property>    
     <property>fcs/parachute_reef_pos_norm</property>
     <value>-0.2</value>
    </product>
   </function>
  <!-- Parachute -->
    
    
  </axis>

  <axis name="DRAG">

    <function name="aero/coefficient/CD0">
       <description>Drag_at_zero_lift</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
             -1.57    1.500
             -0.26    0.025
              0.00    0.019
              0.26    0.025
              1.57    1.500
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/CDi">
       <description>Induced_drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value>0.042</value>
         </product>
    </function>

    <function name="aero/coefficient/CDmach">
       <description>Drag_due_to_mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.79      0.000
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </product>
    </function>

    <function name="aero/coefficient/CDflap">
       <description>Drag_due_to_flaps</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-deg</property>
           <value> 0.00040 </value>
         </product>
    </function>

    <function name="aero/coefficient/CDgear">
       <description>Drag_due_to_gear</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>gear/gear-pos-norm</property>
           <value>0.013</value>
         </product>
    </function>

    <function name="aero/coefficient/CDsb">
       <description>Drag_due_to_speedbrakes</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>0.019</value>
         </product>
    </function>
    
    <function name="aero/coefficient/CDbeta">
       <description>Drag_due_to_sideslip</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <tableData>
              -1.57    1.230
              -0.26    0.050
               0.00    0.000
               0.26    0.050
               1.57    1.230
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/CDde">
       <description>Drag_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-norm</property>
           <value>0.04</value>
       </product>
    </function>

    <!-- Parachute 0.4 war -0.4-->
    <function name="aero/coefficient/CDpc">
    <description>Drag_due_to_chute</description>
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Schute-sqft</property>    
     <property>fcs/parachute_reef_pos_norm</property>
     <value>0.25</value>
    </product>
   </function>
  <!-- Parachute -->
    
  </axis>

  <axis name="SIDE">

    <function name="aero/coefficient/CYb">
       <description>Side_force_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/beta-rad</property>
           <value>-1</value>
       </product>
    </function>

  </axis>

  <axis name="ROLL">

    <function name="aero/coefficient/Clb">
       <description>Roll_moment_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
           <value>-0.1</value>
       </product>
    </function>

    <function name="aero/coefficient/Clp">
       <description>Roll_moment_due_to_roll_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/p-aero-rad_sec</property>
           <value>-0.4</value>
       </product>
    </function>

    <function name="aero/coefficient/Clr">
       <description>Roll_moment_due_to_yaw_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/r-aero-rad_sec</property>
           <value>0.15</value>
       </product>
    </function>

    <function name="aero/coefficient/Clda">
       <description>Roll_moment_due_to_aileron</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/left-aileron-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.100
              2.0    0.033
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/Cldr">
       <description>Roll_moment_due_to_rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>0.01</value>
       </product>
    </function>

    

  </axis>

  <axis name="PITCH">

    <function name="aero/coefficient/Cmalpha">
       <description>Pitch_moment_due_to_alpha</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/alpha-rad</property>
           <value>-0.6</value>
       </product>
    </function>

    <function name="aero/coefficient/Cmde">
       <description>Pitch_moment_due_to_elevator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -1.200
              2.0     -0.300
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/Cmq">
       <description>Pitch_moment_due_to_pitch_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/ci2vel</property>
           <property>velocities/q-aero-rad_sec</property>
           <value>-17</value>
       </product>
    </function>

    <function name="aero/coefficient/Cmadot">
       <description>Pitch_moment_due_to_alpha_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/ci2vel</property>
           <property>aero/alphadot-rad_sec</property>
           <value>-6</value>
       </product>
    </function>
    

  
  </axis>

  <axis name="YAW">

    <function name="aero/coefficient/Cnb">
       <description>Yaw_moment_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
           <value>0.12</value>
       </product>
    </function>

    <function name="aero/coefficient/Cnr">
       <description>Yaw_moment_due_to_yaw_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/r-aero-rad_sec</property>
           <value>-0.15</value>
       </product>
    </function>

    <function name="aero/coefficient/Cndr">
       <description>Yaw_moment_due_to_rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>-0.1</value>
       </product>
    </function>

    <function name="aero/coefficient/Cnda">
       <description>Adverse_yaw</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/left-aileron-pos-rad</property>
           <value>0</value>
       </product>
    </function>

  
    
  </axis>

 </aerodynamics>

 
 <!-- Parachute 0.3 war 1.4--> 
 <external_reactions>
  <force name="parachute" frame="WIND">
    <function>
      <product>
        <property>aero/qbar-psf</property>
        <property>metrics/Schute-sqft</property>
	<property>fcs/parachute_reef_pos_norm</property>
        <value> 0.3 </value> <!-- Full drag coefficient -->
      </product>
    </function>
    <location unit="FT">
      <x> 17.70</x>
      <y> 0</y>
      <z>-1.0</z>
    </location>
    <!-- The direction describes a unit vector. In this case, since
         the selected frame is the WIND frame, the "-1" x component
         describes a direction exactly opposite of the direction
         into the wind vector. That is, the direction specified below
         is the direction that the drag force acts in. -->
    <direction>
      <x>-1</x>
      <y>0</y>
      <z>0</z>
    </direction>
  </force>
 </external_reactions> 
 <!-- Parachute -->
 
 
</fdm_config>