shuttle.xml

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

<!--###################################################################################
    This file is licenced under the terms of the GNU General Public Licence V3 or later
    ###################################################################################
-->

<?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>Thorsten Renk</author>
  <filecreationdate>04-2015</filecreationdate>
  <version>$Revision: 4$</version>
  <description>Space Shuttle Model JSBSim</description>
 </fileheader>



 <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>
	<!-- add the external tank as two masses to get roll inertia-->
	<pointmass name="External_tank1_dry">
            <weight unit="LBS"> 29250.0 </weight>
		<location  unit="M">
		<x> -14.00 </x>
       		<y> -2.50 </y>
       		<z>-10.6 </z>
     		</location>
	</pointmass>
	<pointmass name="External_tank2_dry">
            <weight unit="LBS"> 29250.0 </weight>
		<location unit="M">
		<x> -14.00 </x>
       		<y> 2.50 </y>
       		<z>-10.6 </z>
     		</location>
	</pointmass>
	<pointmass name="SRB-1_dry">
        	<weight unit="LBS"> 181881.0</weight>
		<location unit="M">
			<x> 1.00 </x>
       			<y> -6.10 </y>
       			<z>-10.6 </z>
     		</location>
	</pointmass>
	<pointmass name="SRB-2_dry">
        	<weight unit="LBS"> 181881.0</weight>
		<location unit="M">
			<x> 1.00 </x>
       			<y> 6.10 </y>
       			<z>-10.6 </z>
     		</location>
	</pointmass>
	<pointmass name="Payload">
		<weight unit="LBS"> 0.0</weight>
	 	<location name="POINTMASS" unit="M">
                	<x>  1.0 </x>
                	<y>  0.0 </y>
                	<z> -2.7 </z>
            	</location>
	</pointmass>
	<pointmass name="Docked object">
		<weight unit="LBS"> 0.0</weight>
	 	<location name="POINTMASS" unit="M">
                	<x> -2.7 </x>
                	<y>  0.0 </y>
                	<z> 20.0 </z>
            	</location>
	</pointmass>
 </mass_balance>




 <ground_reactions>

	<contact type="BOGEY" name="NOSE">
		<location unit="M">
			<x> -15.00 </x>
			<y> 0.00 </y>
			<z> -6.87 </z>
		</location>
		<static_friction> 0.40 </static_friction>
		<dynamic_friction> 0.10 </dynamic_friction>
		<rolling_friction> 0.02 </rolling_friction>
		<spring_coeff unit="LBS/FT"> 90000.00 </spring_coeff>
		<damping_coeff unit="LBS/FT/SEC"> 30000.00 </damping_coeff>
		<max_steer unit="DEG"> 15.00 </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>-7.97 </z>
</location>
<static_friction> 0.40 </static_friction>
<dynamic_friction> 0.10 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 550000.00 </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>-7.97 </z>
</location>
<static_friction> 0.40 </static_friction>
<dynamic_friction> 0.10 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 550000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 210000.00 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>RIGHT</brake_group>
<retractable>1</retractable>
</contact>

<contact type="STRUCTURE" name="LEFT_SRB">
<location unit="M">
<x> 18.28 </x>
<y> -4.2 </y>
<z>-14.6 </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"> 3550000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1100000.00 </damping_coeff>
</contact>

<contact type="STRUCTURE" name="RIGHT_SRB">
<location unit="M">
<x> 18.28 </x>
<y> 4.2 </y>
<z>-14.6 </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"> 3550000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1100000.00 </damping_coeff>
</contact>

<contact type="STRUCTURE" name="FICTIONAL CENTER">
<location unit="M">
<x> 18.48 </x>
<y> 0.0 </y>
<z> 4.0 </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"> 1100000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1100000.00 </damping_coeff>
</contact>

<!-- contact points 6, 7-->
<contact type="STRUCTURE" name="LEFT_BODY_FLAP">
<location unit="M">
<x> 15.45 </x>
<y> -2.27 </y>
<z> -4.80 </z>
</location>
<static_friction> 0.50 </static_friction>
<dynamic_friction> 0.20 </dynamic_friction>
<rolling_friction> 0.00 </rolling_friction>
<spring_coeff unit="LBS/FT"> 550000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 110000.00 </damping_coeff>
</contact>

<contact type="STRUCTURE" name="RIGHT_BODY_FLAP">
<location unit="M">
<x> 15.45 </x>
<y> 2.27 </y>
<z> -4.80 </z>
</location>
<static_friction> 0.50 </static_friction>
<dynamic_friction> 0.20 </dynamic_friction>
<rolling_friction> 0.00 </rolling_friction>
<spring_coeff unit="LBS/FT"> 550000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 110000.00 </damping_coeff>
</contact>

<!-- contact points 8, 9, 10-->
<contact type="STRUCTURE" name="LEFT_WING_TIP">
<location unit="M">
<x> 11.35 </x>
<y> -11.99 </y>
<z> -4.81 </z>
</location>
<static_friction> 0.50 </static_friction>
<dynamic_friction> 0.20 </dynamic_friction>
<rolling_friction> 0.00 </rolling_friction>
<spring_coeff unit="LBS/FT"> 550000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 110000.00 </damping_coeff>
</contact>

<contact type="STRUCTURE" name="RIGHT_WING_TIP">
<location unit="M">
<x> 11.35 </x>
<y> 11.99 </y>
<z> -4.81 </z>
</location>
<static_friction> 0.50 </static_friction>
<dynamic_friction> 0.20 </dynamic_friction>
<rolling_friction> 0.00 </rolling_friction>
<spring_coeff unit="LBS/FT"> 550000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 110000.00 </damping_coeff>
</contact>

<contact type="STRUCTURE" name="NOSE_CONE">
<location unit="M">
<x> -18.92 </x>
<y> 0.0 </y>
<z> -4.90 </z>
</location>
<static_friction> 0.50 </static_friction>
<dynamic_friction> 0.20 </dynamic_friction>
<rolling_friction> 0.00 </rolling_friction>
<spring_coeff unit="LBS/FT"> 550000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 110000.00 </damping_coeff>
</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>-->

 

 </ground_reactions>

 <propulsion>


   <!--SSME  -->

   <engine file="SSME">
    <location unit="M">
      <x> 17.00 </x>
      <y>   -1.35 </y>
      <z>   -3.45 </z>
    </location>
    <orient unit="DEG">
      <pitch> -16.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>    
    <thruster file="SSME_nozzle">
     <location unit="M">
      <x> 17.00 </x>
      <y>   -1.35 </y>
      <z>   -3.45 </z>
     </location>
     <orient unit="DEG">
       <pitch> -16.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>   

  <engine file="SSME">
    <location unit="M">
      <x> 17.00 </x>
      <y>   1.35 </y>
      <z>   -3.45 </z>
    </location>
    <orient unit="DEG">
      <pitch> -16.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>    
    <thruster file="SSME_nozzle">
     <location unit="M">
      <x> 17.00 </x>
      <y>   1.35 </y>
      <z>   -3.45 </z>
     </location>
     <orient unit="DEG">
       <pitch> -16.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>   

  <engine file="SSME">
    <location unit="M">
      <x> 17.00 </x>
      <y>   0.00 </y>
      <z>   -1.0 </z>
    </location>
    <orient unit="DEG">
      <pitch> -16.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>    
    <thruster file="SSME_nozzle">
     <location unit="M">
      <x> 17.00 </x>
      <y>   0.00 </y>
      <z>   -1.0 </z>
     </location>
     <orient unit="DEG">
       <pitch> -16.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>   



<!-- external tank -->
  <tank type="FUEL" number="0">
     <location unit="M">
       <x> -15.00 </x>
       <y> 0.00 </y>
       <z>-10.6 </z>
     </location>
     <capacity unit="LBS"> 1618634.00 </capacity>
     <contents unit="LBS"> 1618634.00 </contents>
     <priority>1</priority>
  </tank>
 
 


<!-- SRB -->


   <engine file="SRB">
    <location unit="M">
      <x> 18.28 </x>
      <y>  -6.10 </y>
      <z>-10.6 </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="M">
      <x> 18.28 </x>
      <y>  -6.10 </y>
      <z>-10.6 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <tank type="FUEL" number="1">
     <location unit="M">
       <x> 1.00 </x>
       <y> -6.10 </y>
       <z>-10.6 </z>
     </location>
      <capacity unit="LBS">1114092.6</capacity>
      <contents unit="LBS">1114092.6</contents>
  </tank>

 <engine file="SRB">
    <location unit="M">
      <x> 18.28 </x>
      <y>  6.10 </y>
      <z>-10.6 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>    
    <feed>2</feed>  
    <thruster file="SRB_nozzle">
     <location unit="M">
      <x> 18.28 </x>
      <y>  6.10 </y>
      <z>-10.6 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <tank type="FUEL" number="2">
     <location unit="M">
       <x> 1.00 </x>
       <y> 6.10 </y>
       <z>-10.6 </z>
     </location>
      <capacity unit="LBS">1114092.6</capacity>
      <contents unit="LBS">1114092.6</contents>
  </tank>

<!-- this will later be the ET oxidizer - now we just reserve the index -->

 <tank type="FUEL" number="3">
     <location unit="M">
       <x> -15.00 </x>
       <y> 0.00 </y>
       <z>-10.6 </z>
     </location>
     <capacity unit="LBS"> 10.00 </capacity>
     <contents unit="LBS"> 0.00 </contents>
     <priority>1</priority>
  </tank>  

<!-- OMS -->

   <!-- left OMS thruster -->

   <engine file="OMS">
    <location unit="M">
      <x> 17.0 </x>
       <y> -2.2 </y>
       <z> 0.27 </z>
    </location>
    <orient unit="DEG">
      <pitch> 4.0 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>    
    <feed>4</feed>   
    <feed>5</feed>     
    <thruster file="OMS_nozzle">
     <location unit="M">
      <x> 17.0 </x>
       <y> -2.2 </y>
       <z> 0.27 </z>
    </location>
     <orient unit="DEG">
       <pitch> 4.0 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
    </engine>

   <!-- right OMS thruster -->

   <engine file="OMS">
    <location unit="M">
      <x> 17.0 </x>
       <y> 2.2 </y>
       <z> 0.27 </z>
    </location>
    <orient unit="DEG">
      <pitch> 4.0 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>    
     <feed>6</feed>   
     <feed>7</feed>     
    <thruster file="OMS_nozzle">
     <location unit="M">
      <x> 17.0 </x>
       <y> 2.2 </y>
       <z> 0.27 </z>
    </location>
     <orient unit="DEG">
       <pitch> 4.0 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
    </engine>


 <!-- left OMS pod tank -->
 
  <tank type="OXIDIZER" number="4">
     <location unit="M">
       <x>  14.00 </x>
       <y> -2.20 </y>
       <z>  0.27 </z>
     </location>
     <capacity unit="LBS"> 7773.00 </capacity>
     <contents unit="LBS"> 7773.00 </contents>
     <priority>2</priority>
  </tank>

  <tank type="FUEL" number="5">
     <location unit="M">
       <x> 14.00 </x>
       <y> -2.20 </y>
       <z> 0.27 </z>
     </location>
     <capacity unit="LBS"> 4718.00 </capacity>
     <contents unit="LBS"> 4718.00 </contents>
     <priority>2</priority>
  </tank>

 <!-- right OMS pod tank-->

  <tank type="OXIDIZER" number="6">
     <location unit="M">
       <x> 14.00 </x>
       <y> 2.20 </y>
       <z> 0.27 </z>
     </location>
     <capacity unit="LBS"> 7773.00 </capacity>
     <contents unit="LBS"> 7773.00 </contents>
     <priority>2</priority>
  </tank>

  <tank type="FUEL" number="7">
     <location unit="M">
       <x> 14.00 </x>
       <y> 2.20 </y>
       <z> 0.27 </z>
     </location>
     <capacity unit="LBS"> 4718.00 </capacity>
     <contents unit="LBS"> 4718.00 </contents>
     <priority>2</priority>
  </tank>


 
<!-- RCS thrusters -->

<!-- the normal thrusters - ISP 289 s, nominal thrust about 870 lb each -->


<!-- F2F - rightmost forward-pointing thruster of nose module -->

  <engine file="RCS-887.9lb">
    <location unit="M">
      <x>-15.0</x>
      <y>0.4</y>
      <z>-3.2</z>
    </location>
    <orient unit="DEG">
      <pitch>-7.80 </pitch>
      <roll>   0.00 </roll>
      <yaw> 181.70    </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>0.4</y>
      <z>-3.2</z>
      </location>
     <orient unit="DEG">
       <pitch>-7.80 </pitch>
       <roll>   0.00 </roll>
       <yaw> 181.7 </yaw>
     </orient>
    </thruster>
  </engine>



<!-- F3F - middle forward-pointing thuster of nose module-->

  <engine file="RCS-887.9lb">
    <location unit="M">
      <x>-15.0</x>
      <y>0.0</y>
      <z>-3.2</z>
    </location>
    <orient unit="DEG">
      <pitch>-8.0 </pitch>
      <roll>   0.00 </roll>
      <yaw>  180 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>0.0</y>
      <z>-3.2</z>
      </location>
     <orient unit="DEG">
       <pitch>-8.0 </pitch>
       <roll>   0.00 </roll>
       <yaw>  180.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F1F - leftmost forward-pointing thruster of nose module-->

  <engine file="RCS-887.9lb">
    <location unit="M">
      <x>-15.0</x>
      <y>-0.4</y>
      <z>-3.2</z>
    </location>
    <orient unit="DEG">
      <pitch> -7.80</pitch>
      <roll>   0.00 </roll>
      <yaw>   178.30 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>-0.4</y>
      <z>-3.2</z>
      </location>
     <orient unit="DEG">
       <pitch>-7.80 </pitch>
       <roll>   0.00 </roll>
       <yaw>  178.30 </yaw>
     </orient>
    </thruster>

  </engine>

<!-- F1L - upper left-pointing thruster of nose module -->


   <engine file="RCS-874.2lb">
    <location unit="M">
      <x>-15.0</x>
      <y>-0.8</y>
      <z>-3.4</z>
    </location>
    <orient unit="DEG">
      <pitch>-1.20 </pitch>
      <roll>   0.00 </roll>
      <yaw>   91.7 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>-0.8</y>
      <z>-3.4</z>
      </location>
     <orient unit="DEG">
       <pitch>-1.20 </pitch>
       <roll>   0.00 </roll>
       <yaw>    91.7 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F3L - lower left-pointing thruster of nose module -->
 

  <engine file="RCS-870.6lb">
    <location unit="M">
      <x>-15.0</x>
      <y>-0.8</y>
      <z>-3.8</z>
    </location>
    <orient unit="DEG">
      <pitch>  0.0 </pitch>
      <roll>   0.00 </roll>
      <yaw>   91.4 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>-0.8</y>
      <z>-3.8</z>
      </location>
     <orient unit="DEG">
       <pitch>  0.0 </pitch>
       <roll>   0.00 </roll>
       <yaw>    91.4 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F2R - upper right-pointing thruster of nose module -->


<engine file="RCS-874.2lb">
    <location unit="M">
      <x>-15.0</x>
      <y>0.8</y>
      <z>-3.4</z>
    </location>
    <orient unit="DEG">
      <pitch>-1.20 </pitch>
      <roll>   0.00 </roll>
      <yaw>   -91.7 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>0.8</y>
      <z>-3.4</z>
      </location>
     <orient unit="DEG">
       <pitch>-1.20 </pitch>
       <roll>   0.00 </roll>
       <yaw>    -91.7 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F4R - forward right-pointing thruster of nose module -->

 <engine file="RCS-870.6lb">
    <location unit="M">
      <x>-15.0</x>
      <y>0.8</y>
      <z>-3.8</z>
    </location>
    <orient unit="DEG">
      <pitch>  0.0 </pitch>
      <roll>   0.00 </roll>
      <yaw>   -91.4 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>0.8</y>
      <z>-3.8</z>
      </location>
     <orient unit="DEG">
       <pitch>  0.0 </pitch>
       <roll>   0.00 </roll>
       <yaw>    -91.4 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F2U - rightmost upward-pointing thruster of nose module -->

 <engine file="RCS-875.1lb">
    <location unit="M">
      <x>-15.0</x>
      <y>0.4</y>
      <z>-3.2</z>
    </location>
    <orient unit="DEG">
      <pitch> -87.76 </pitch>
      <roll>   0.00 </roll>
      <yaw>   199.91 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>0.4</y>
      <z>-3.2</z>
      </location>
     <orient unit="DEG">
       <pitch> -87.76 </pitch>
       <roll>   0.00 </roll>
      <yaw>   199.91 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F3U - middle upward-pointing thruster of nose module -->

 <engine file="RCS-874.2lb">
    <location unit="M">
      <x>-15.0</x>
      <y>0.0</y>
      <z>-3.2</z>
    </location>
    <orient unit="DEG">
      <pitch> -87.91 </pitch>
      <roll>   0.00 </roll>
      <yaw>   180.00 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>0.0</y>
      <z>-3.2</z>
      </location>
     <orient unit="DEG">
       <pitch> -87.91 </pitch>
       <roll>   0.00 </roll>
       <yaw>   180.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F1U -leftmost upward-pointing thruster of nose module -->

 <engine file="RCS-875.1lb">
    <location unit="M">
      <x>-15.0</x>
      <y>-0.4</y>
      <z>-3.2</z>
    </location>
    <orient unit="DEG">
      <pitch> -87.76 </pitch>
      <roll>   0.00 </roll>
      <yaw>   160.09 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.0</x>
      <y>-0.4</y>
      <z>-3.2</z>
      </location>
     <orient unit="DEG">
       <pitch> -87.76 </pitch>
       <roll>   0.00 </roll>
      <yaw>   160.09 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F2D - front right-downward-pointing thruster of nose module -->

<engine file="RCS-896.6lb">
    <location unit="M">
      <x>-15.2</x>
      <y>0.8</y>
      <z>-3.4</z>
    </location>
    <orient unit="DEG">
      <pitch> 46.6 </pitch>
      <roll>   0.00 </roll>
      <yaw>   -91.8 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.2</x>
      <y>0.8</y>
      <z>-3.4</z>
      </location>
     <orient unit="DEG">
       <pitch> 46.6 </pitch>
       <roll>   0.00 </roll>
       <yaw>   -91.8 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F1D - front left-downward-pointing thruster of nose module -->


<engine file="RCS-896.6lb">
    <location unit="M">
      <x>-15.2</x>
      <y>-0.8</y>
      <z>-3.4</z>
    </location>
    <orient unit="DEG">
      <pitch> 46.6 </pitch>
      <roll>   0.00 </roll>
      <yaw>   91.8 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.2</x>
      <y>-0.8</y>
      <z>-3.4</z>
      </location>
     <orient unit="DEG">
       <pitch> 46.6 </pitch>
       <roll>   0.00 </roll>
       <yaw>   91.8 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F4D - rear right-downward pointing thruster of nose module -->

<engine file="RCS-885.9lb">
    <location unit="M">
      <x>-14.8</x>
      <y>0.8</y>
      <z>-3.4</z>
    </location>
    <orient unit="DEG">
      <pitch> 46.9 </pitch>
      <roll>   0.00 </roll>
      <yaw>   -91.6 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-14.8</x>
      <y>0.8</y>
      <z>-3.4</z>
      </location>
     <orient unit="DEG">
       <pitch> 46.9 </pitch>
       <roll>   0.00 </roll>
       <yaw>   -91.6 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F3D - rear left-downward pointing thruster of nose module -->

<engine file="RCS-885.9lb">
    <location unit="M">
      <x>-14.8</x>
      <y>-0.8</y>
      <z>-3.4</z>
    </location>
    <orient unit="DEG">
      <pitch> 46.9 </pitch>
      <roll>   0.00 </roll>
      <yaw>   91.6 </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-14.8</x>
      <y>-0.8</y>
      <z>-3.4</z>
      </location>
     <orient unit="DEG">
       <pitch> 46.9 </pitch>
       <roll>   0.00 </roll>
       <yaw>   91.6 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- the thrusters of the pod modules are somewhat closer together, we give them 30 cm spacing -->

<!-- R3A - rightmost backward-pointing thruster of right OMS pod module -->


 <engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>3.35</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -10.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>3.35</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>-10.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R1A - left backward-pointing thruster of right OMS pod module -->

 <engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>3.05</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -10.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>3.05</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>-10.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L3A - left backward-pointing thruster of left OMS pod module -->


 <engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>-3.35</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -10.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>-3.35</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>-10.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L1A - right backward-pointing thruster of left OMS pod module -->

 <engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>-3.05</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -10.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>-3.05</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>-10.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L4L - foremost left-pointing thruster of left OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>16.55</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.47 </pitch>
      <roll>   0.00 </roll>
      <yaw>    90.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>16.55</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.47 </pitch>
       <roll> 0.00 </roll>
       <yaw>  90.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L2L - second foremost left-pointing thruster of left OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>16.85</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.47 </pitch>
      <roll>   0.00 </roll>
      <yaw>    90.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>16.85</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.47 </pitch>
       <roll> 0.00 </roll>
       <yaw>  90.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L3L - second-to-last left-pointing thruster of left OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.15</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.47 </pitch>
      <roll>   0.00 </roll>
      <yaw>    90.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.15</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.47 </pitch>
       <roll> 0.00 </roll>
       <yaw>  90.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L1L - rearmost left-pointing thruster of left OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.47 </pitch>
      <roll>   0.00 </roll>
      <yaw>    90.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.47 </pitch>
       <roll> 0.00 </roll>
       <yaw>  90.00 </yaw>
     </orient>
    </thruster>
  </engine>


<!-- R4R - foremost right-pointing thruster of right OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>16.55</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.47 </pitch>
      <roll>   0.00 </roll>
      <yaw>    -90.00 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>16.55</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.47 </pitch>
       <roll> 0.00 </roll>
       <yaw>  -90.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R2R - second foremost right-pointing thruster of right OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>16.85</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.47 </pitch>
      <roll>   0.00 </roll>
      <yaw>    -90.00 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>16.85</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.47 </pitch>
       <roll> 0.00 </roll>
       <yaw>  -90.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R3R - second-to-last right-pointing thruster of right OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.15</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.47 </pitch>
      <roll>   0.00 </roll>
      <yaw>    -90.00 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.15</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.47 </pitch>
       <roll> 0.00 </roll>
       <yaw>  -90.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R1R - rearmost right-pointing thruster of right OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.47 </pitch>
      <roll>   0.00 </roll>
      <yaw>    -90.00 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.47 </pitch>
       <roll> 0.00 </roll>
       <yaw>  -90.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L4U - foremost upward-pointing thruster of left OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>16.85</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>16.85</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> -90.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L2U - middle upward-pointing thruster of left OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.15</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.15</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> -90.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L1U - rearmost upward-pointing thruster of left OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> -90.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R4U - foremost upward-pointing thruster of right OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>16.85</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>16.85</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> -90.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R2U - middle upward-pointing thruster of right OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.15</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.15</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> -90.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R1U - rearmost upward-pointing thruster of right OMS pod module -->

<engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  -90.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.00 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> -90.00 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L4D -foremost downward pointing thruster of left OMS pod module -->

  <engine file="RCS-870.0lb">
    <location unit="M">
      <x>16.85</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  67.15 </pitch>
      <roll>   0.00 </roll>
      <yaw>    50.80 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>16.85</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> 67.15 </pitch>
       <roll> 0.00 </roll>
       <yaw>  50.80 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L2D - middle downward pointing thruster of left OMS pod module -->

  <engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.15</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  67.15 </pitch>
      <roll>   0.00 </roll>
      <yaw>    50.80 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.15</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> 67.15 </pitch>
       <roll> 0.00 </roll>
       <yaw>  50.80 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L3D - rear downward pointing thruster of left OMS pod module -->

  <engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  67.15 </pitch>
      <roll>   0.00 </roll>
      <yaw>    50.80 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> 67.15 </pitch>
       <roll> 0.00 </roll>
       <yaw>  50.80 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R4D -foremost downward pointing thruster of right OMS pod module -->

  <engine file="RCS-870.0lb">
    <location unit="M">
      <x>16.85</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  67.15 </pitch>
      <roll>   0.00 </roll>
      <yaw>    -50.80 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>16.85</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> 67.15 </pitch>
       <roll> 0.00 </roll>
       <yaw>  -50.80 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R2D - middle downward pointing thruster of right OMS pod module -->

  <engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.15</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  67.15 </pitch>
      <roll>   0.00 </roll>
      <yaw>    -50.80 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.15</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> 67.15 </pitch>
       <roll> 0.00 </roll>
       <yaw>  -50.80 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R3D - rear downward pointing thruster of right OMS pod module -->

  <engine file="RCS-870.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  67.15 </pitch>
      <roll>   0.00 </roll>
      <yaw>    -50.80 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> 67.15 </pitch>
       <roll> 0.00 </roll>
       <yaw>  -50.80 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- the Vernier thrusters - ISP 228 s, nominal thrust about 24 lb each -->

<!-- F5R - right-downward pointing Vernier of nose module -->

 <engine file="RCS-24.5lb">
    <location unit="M">
      <x>-15.4</x>
      <y>0.8</y>
      <z>-3.8</z>
    </location>
    <orient unit="DEG">
      <pitch> 46.0 </pitch>
      <roll>  0.00 </roll>
      <yaw>  -91.8    </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.4</x>
      <y>0.8</y>
      <z>-3.8</z>
      </location>
     <orient unit="DEG">
       <pitch>46.0 </pitch>
       <roll> 0.0 </roll>
       <yaw>  -91.8 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- F5L - left-downward pointing Vernier of nose module -->

 <engine file="RCS-24.5lb">
    <location unit="M">
      <x>-15.4</x>
      <y>-0.8</y>
      <z>-3.8</z>
    </location>
    <orient unit="DEG">
      <pitch> 46.0 </pitch>
      <roll>  0.00 </roll>
      <yaw>  91.8    </yaw>
    </orient>
    <feed>12</feed>
    <feed>13</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>-15.4</x>
      <y>-0.8</y>
      <z>-3.8</z>
      </location>
     <orient unit="DEG">
       <pitch>46.0 </pitch>
       <roll> 0.0 </roll>
       <yaw>  91.8 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L5D - downward pointing Vernier of left OMS pod module -->

 <engine file="RCS-24.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  90.0 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.0 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> 90.0 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.0 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R5D - downward pointing Vernier of right OMS pod module -->

 <engine file="RCS-24.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  90.0 </pitch>
      <roll>   0.00 </roll>
      <yaw>    0.0 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch> 90.0 </pitch>
       <roll> 0.00 </roll>
       <yaw>  0.0 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- L5L - left pointing Vernier of left OMS pod module -->

 <engine file="RCS-24.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.4 </pitch>
      <roll>   0.00 </roll>
      <yaw>    90.0 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>-3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.4 </pitch>
       <roll> 0.00 </roll>
       <yaw>  90.0 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- R5R - right pointing Vernier of right OMS pod module -->

 <engine file="RCS-24.0lb">
    <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
    </location>
    <orient unit="DEG">
      <pitch>  1.4 </pitch>
      <roll>   0.00 </roll>
      <yaw>    -90.0 </yaw>
    </orient>
    <feed>10</feed>
    <feed>11</feed>    
    <thruster file="RCS_nozzle">     
      <location unit="M">
      <x>17.45</x>
      <y>3.2</y>
      <z>-0.5</z>
      </location>
     <orient unit="DEG">
       <pitch>1.4 </pitch>
       <roll> 0.00 </roll>
       <yaw>  -90.0 </yaw>
     </orient>
    </thruster>
  </engine>






 
 <!-- RCS tanks - -->
 
 <!-- left OMS pod -->

    <tank type="OXIDIZER" number="8">
     <location unit="M">
       <x> 12.00 </x>
       <y> -2.20 </y>
       <z> 0.27 </z>
     </location>
     <capacity unit="LBS"> 1477.00 </capacity>
     <contents unit="LBS"> 1477.00 </contents>
     <priority>2</priority>
  </tank>

  <tank type="FUEL" number="9">
     <location unit="M">
       <x> 12.00 </x>
       <y> -2.20 </y>
       <z> 0.27 </z>
     </location>
     <capacity unit="LBS"> 928.00 </capacity>
     <contents unit="LBS"> 928.00 </contents>
     <priority>2</priority>
  </tank>

 <!-- right OMS pod -->

   <tank type="OXIDIZER" number="10">
     <location unit="M">
       <x> 12.00 </x>
       <y> 2.20 </y>
       <z> 0.27 </z>
     </location>
     <capacity unit="LBS"> 1477.00 </capacity>
     <contents unit="LBS"> 1477.00 </contents>
     <priority>2</priority>
  </tank>

  <tank type="FUEL" number="11">
     <location unit="M">
       <x> 12.00 </x>
       <y> 2.20 </y>
       <z> 0.27 </z>
     </location>
     <capacity unit="LBS"> 928.00 </capacity>
     <contents unit="LBS"> 928.00 </contents>
     <priority>2</priority>
  </tank>

 <!-- nose module pod -->

   <tank type="OXIDIZER" number="12">
     <location unit="M">
       <x> -15.50 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 1477.00 </capacity>
     <contents unit="LBS"> 1477.00 </contents>
     <priority>2</priority>
  </tank>

  <tank type="FUEL" number="13">
     <location unit="M">
       <x> -15.50 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 928.00 </capacity>
     <contents unit="LBS"> 928.00 </contents>
     <priority>2</priority>
   </tank>

<!-- Hydrazine tanks for the three APUs -->
 
<tank type="FUEL" number="14">
     <location unit="M">
       <x> -8.50 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 350.00 </capacity>
     <contents unit="LBS"> 350.00 </contents>
     <priority>2</priority>
   </tank>

<tank type="FUEL" number="15">
     <location unit="M">
       <x> -8.50 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 350.00 </capacity>
     <contents unit="LBS"> 350.00 </contents>
     <priority>2</priority>
   </tank>

<tank type="FUEL" number="16">
     <location unit="M">
       <x> -8.50 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 350.00 </capacity>
     <contents unit="LBS"> 350.00 </contents>
     <priority>2</priority>
   </tank>

<!-- virtual tanks to simulate fuel trapped in the feed lines, to be dumped after MECO --> 

  <tank type="FUEL" number="17">
     <location unit="M">
       <x> 14.00 </x>
       <y>  0.00 </y>
       <z> -2.50 </z>
     </location>
     <capacity unit="LBS"> 600.00 </capacity>
     <contents unit="LBS"> 0.00 </contents>
     <priority>2</priority>
  </tank>

  <tank type="OXIDIZER" number="18">
     <location unit="M">
       <x> 14.00 </x>
       <y>  0.00 </y>
       <z> -2.50 </z>
     </location>
     <capacity unit="LBS"> 4800.00 </capacity>
     <contents unit="LBS"> 0.00 </contents>
     <priority>2</priority>
  </tank>


<!-- four water tanks with 165 lb capacity each for flash evaporator system --> 

  <tank type="FUEL" number="19">
     <location unit="M">
       <x> 0.00 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 660.00 </capacity>
     <contents unit="LBS"> 660.00 </contents>
     <priority>2</priority>
   </tank>

<!-- water tanks for the three APU water spray boilers -->


  <tank type="FUEL" number="20">
     <location unit="M">
       <x> 0.00 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 142.00 </capacity>
     <contents unit="LBS"> 142.00 </contents>
     <priority>2</priority>
   </tank>

  <tank type="FUEL" number="21">
     <location unit="M">
       <x> 0.00 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 142.00 </capacity>
     <contents unit="LBS"> 142.00 </contents>
     <priority>2</priority>
   </tank>

  <tank type="FUEL" number="22">
     <location unit="M">
       <x> 0.00 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 142.00 </capacity>
     <contents unit="LBS"> 142.00 </contents>
     <priority>2</priority>
   </tank>

<!-- virtual fuel tank modeling for cabin air pressure -->

  <!-- oxygen content -->
  <tank type="FUEL" number="23">
     <location unit="M">
       <x> 0.00 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 45.00 </capacity>
     <contents unit="LBS"> 40.00 </contents>
     <priority>2</priority>
   </tank>

  <!-- nitrogen content -->
  <tank type="FUEL" number="24">
     <location unit="M">
       <x> 0.00 </x>
       <y> 0.00 </y>
       <z> -3.60 </z>
     </location>
     <capacity unit="LBS"> 147.00 </capacity>
     <contents unit="LBS"> 130.00 </contents>
     <priority>2</priority>
   </tank>


 </propulsion>

<!-- Flight Control routines - this block has airfoils -->
<!--  thrust vectoring and the RCS are defined under Systems -->


 <flight_control name="FCS: shuttle">

  <channel name="Launch Config">
  <switch name="Aerodynamics for launch vehicle">
			<default value="0.0"/>
			<test value="1.0">
			inertia/pointmass-weight-lbs[1] GT 0.0
			</test>
	<output>aero/launch-config</output>
  </switch>

  <switch name="Aerodynamics for orbiter">
			<default value="0.0"/>
			<test value="1.0">
			inertia/pointmass-weight-lbs[1] == 0.0
			</test>
	<output>aero/orbiter-config</output>
  </switch>

  </channel>
  
  <channel name="Control Config">

  <switch name="systems/fcs/airfoil-rate-control">
			<default value="0.0"/>
			<test value="1.0">
				systems/fcs/control-mode == 29
			</test>
   </switch>

  </channel>

  <channel name="Actuator stall">
  
  <fcs_function name="systems/fcs/actuator-stall-factor">
  <function>
	<max>
	<difference>
	<value>1.0</value>
	<quotient>
		<max>
		<difference>
			<property>aero/qbar-psf</property>
			<property>systems/various/qbar-limit-entry</property>
		</difference>
		<value>0.0</value>
		</max>
		<value>200.0</value>
	</quotient>
	</difference>
	<value>0.0</value>
	<property>systems/ap/grtls/Nz-hold-active</property>
	</max>
  </function>
  </fcs_function>

  </channel>

 <channel name="Flight controller power">
 
 <!-- check view number and assume we're using PLT stick when in pilot view -->

 <switch name="fcs/controller-power">
	<default value="0.0"/>
	<test logic="AND" value="1.0">
		fcs/controller-power-plt == 1
		/sim/current-view/view-number == 13
		systems/failures/rhc-plt-condition == 1
	</test>
	<test logic="AND" value="1.0">
		fcs/controller-power-cdr == 1
		/sim/current-view/view-number NE 13
		systems/failures/rhc-cdr-condition == 1
	</test>
 </switch>
 

 <fcs_function name="fcs/elevator-cmd-norm-css">
 <function>
 	<product>
		<property>fcs/elevator-cmd-norm</property>
		<property>fcs/controller-power</property>
	</product>
 </function>
 </fcs_function>

 <fcs_function name="fcs/rudder-cmd-norm-css">
 <function>
 	<product>
		<property>fcs/rudder-cmd-norm</property>
		<property>fcs/controller-power</property>
	</product>
 </function>
 </fcs_function>

 <fcs_function name="fcs/aileron-cmd-norm-css">
 <function>
 	<product>
		<property>fcs/aileron-cmd-norm</property>
		<property>fcs/controller-power</property>
	</product>
 </function>
 </fcs_function>

 </channel>


  <channel name="Pitch">

  <switch name="Disable airfoil pitch if thrust vectoring is used">
			<default value="1.0"/>
			<test logic="OR" value="0.0">
				systems/fcs/control-mode == 0
				systems/fcs/control-mode == 10
				systems/fcs/control-mode == 11
				systems/fcs/control-mode == 13
				systems/fcs/control-mode == 1
				systems/fcs/control-mode == 2
				systems/fcs/control-mode == 3
				systems/fcs/control-mode == 20
				systems/fcs/control-mode == 21
				systems/fcs/control-mode == 22
				systems/fcs/control-mode == 23
				systems/fcs/control-mode == 25
				systems/fcs/control-mode == 26
				systems/fcs/control-mode == 27
				systems/fcs/control-mode == 28
			</test>
		<output>fcs/airfoil-factor-pitch-base</output>
   </switch>

   <fcs_function name="fcs/airfoil-factor-pitch">
   <function>
	<product>
		<property>fcs/airfoil-factor-pitch-base</property>
		<property>systems/fcs/actuator-stall-factor</property>
	</product>
   </function>
   </fcs_function>


   <fcs_function name="Pitch Auto Trim">
	<function>
	<product>
	<table>
        	<independentVar lookup="row">velocities/mach</independentVar>
        	<tableData>
          	 0.0     0.00
          	 5.0     0.00
	 	  10.0	   -0.1
		   20.0	   -0.2
        	</tableData>
      	</table>
	<property>aero/orbiter-config</property>
	</product>
	</function>
   </fcs_function>

  <fcs_function name="Launch Auto Trim">
	<function>
	<product>
	<table>
        	<independentVar lookup="row">velocities/mach</independentVar>
        	<tableData>
          	0.0	0.2
		1.5	0.2
		2.5	0.0
        	</tableData>
      	</table>
	<property>aero/launch-config</property>
	</product>
	</function>
   </fcs_function>

   <switch name="fcs/ap/auto-elevator-cmd-norm">
	<default value="0.0"/>
	<test  value="systems/ap/alpha-controller-elevator-cmd-norm">
		systems/ap/auto-entry-active == 1
	</test>
	<test  value="systems/ap/taem/taem-controller-elevator-cmd-norm">
		systems/ap/auto-taem-active == 1
	</test>
	<test  value="systems/ap/grtls/pitch-cmd">
		systems/ap/auto-grtls-active == 1
	</test>
   </switch>

   <switch name="fcs/ap/auto-pitch-active">
	<default value="0.0"/>
	<test logic="AND" value="1.0">
		systems/ap/auto-entry-active == 1
		systems/ap/automatic-pitch-control == 1
	</test>
	<test logic="AND" value="1.0">
		systems/ap/auto-taem-active == 1
		systems/ap/automatic-pitch-control == 1
	</test>
	<test logic="AND" value="1.0">
		systems/ap/auto-grtls-active == 1
		systems/ap/automatic-pitch-control == 1
	</test>
   </switch>

   <fcs_function name="fcs/elevator-ap-cmd-merge">
   <function>
	<sum>
		<product>
			<difference>
				<value>1</value>
				<property>fcs/ap/auto-pitch-active</property>
			</difference>
			<property>fcs/elevator-cmd-norm-css</property>
		</product>
		<product>
			<property>fcs/ap/auto-pitch-active</property>
			<property>fcs/ap/auto-elevator-cmd-norm</property>
		</product>
	</sum>
   </function>
   </fcs_function>

   <fcs_function name="fcs/pitch-error">
	 <function>
	 	<difference>
			<property>velocities/q-rad_sec</property>
			<product>
				<property>fcs/elevator-ap-cmd-merge</property>
				<value>-0.3</value>
			</product>
		</difference>
	</function>
  </fcs_function>

  <deadband name="fcs/pitch-PID-trigger-raw">
	<input>fcs/pitch-error</input>
	<width>0.2</width>
  </deadband>

  <fcs_function name="fcs/pitch-PID-trigger">
  <function>
	<max>
	<property>/fdm/jsbsim/systems/fcs/rcs-pitch-mode</property>
	<property>fcs/pitch-PID-trigger-raw</property>
	<difference>
		<value>1.0</value>
		<property>systems/fcs/airfoil-rate-control</property>
	</difference>
	<property>systems/ap/grtls/Nz-hold-active</property>
	</max>
  </function>
  </fcs_function>

  <pid name="fcs/pitch-controller">
	<input>fcs/pitch-error</input>
	<kp> 30.0 </kp>
	<ki> 5.0 </ki>
	<kd> 15.0</kd>
	<trigger>fcs/pitch-PID-trigger</trigger>
	<clipto>
		<min> -1.0 </min>
        	<max>  1.0 </max>
	</clipto>
  </pid>

  <fcs_function name="fcs/pitch-command">
  <function>
	<sum>
	<product>
		<property>systems/fcs/airfoil-rate-control</property>
		<property>fcs/pitch-controller</property>
	</product>
	<product>
		<difference>
			<value>1.0</value>
			<property>systems/fcs/airfoil-rate-control</property>	
		</difference>
		<property>fcs/elevator-cmd-norm-css</property>
	</product>
	</sum>
  </function>
  </fcs_function>

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

   <aerosurface_scale name="Elevator Control">
      <input>fcs/pitch-trim-sum</input>
      <range>
        <min> -0.70 </min>
        <max>  0.44 </max>
      </range>
      <output>fcs/elevator-pos-rad-trim</output>
   </aerosurface_scale>

   <!--<pure_gain name="Actual Elevator Motion">
	<input>fcs/elevator-pos-rad-command</input>
	<gain>fcs/airfoil-factor-pitch</gain>
	<output>fcs/elevator-pos-rad</output>
   </pure_gain>-->

   <fcs_function name="Actual Elevator Motion">
	<function>
	<product>
	<sum>
		<product>
			<property>fcs/elevator-pos-rad-trim</property>
			<property>fcs/airfoil-factor-pitch</property>
		</product>
		<property>fcs/launch-auto-trim</property>
	</sum>
	<property>systems/failures/airfoils-pitch-condition</property>
	<property>systems/apu/hyd-pressure-available</property>
	</product>
	</function>
	<output>fcs/elevator-pos-rad-command</output>
   </fcs_function>

   <!-- Priority rate limiting dependent on number of available hydraulics systems -->

   <kinematic name="Elevator Movement PRL 3 and 2">
	<input>fcs/elevator-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>2.85</time>
		</setting>
		</traverse>
	<output>fcs/elevator-pos-prl32-rad</output>
   </kinematic>

   <kinematic name="Elevator Movement PRL 1">
	<input>fcs/elevator-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>4.10</time>
		</setting>
		</traverse>
	<output>fcs/elevator-pos-prl1-rad</output>
   </kinematic>

   <switch name="Priority rate limiting elevator">
			<default value="0.0"/>
			<test logic="OR" value="fcs/elevator-pos-prl32-rad">
				systems/apu/number-systems-pressurized == 3
				systems/apu/number-systems-pressurized == 2
			</test>
			<test value="fcs/elevator-pos-prl1-rad">
				systems/apu/number-systems-pressurized == 1
			</test>
	<output>fcs/elevator-pos-rad</output>
   </switch>


   <aerosurface_scale name="Elevator Normalization">
      <input>fcs/elevator-pos-rad-command</input>
      <domain>
        <min> -0.70 </min>
        <max>  0.44 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/elevator-pos-norm</output>
   </aerosurface_scale>

  </channel>



  <channel name="Roll">

  <switch name="Disable airfoil roll if thrust vectoring is used">
			<default value="1.0"/>
			<test logic="OR" value="0.0">
				systems/fcs/control-mode == 0
				systems/fcs/control-mode == 10
				systems/fcs/control-mode == 11
				systems/fcs/control-mode == 1
				systems/fcs/control-mode == 2
				systems/fcs/control-mode == 3
				systems/fcs/control-mode == 20
				systems/fcs/control-mode == 21
				systems/fcs/control-mode == 22
				systems/fcs/control-mode == 23
				systems/fcs/control-mode == 25
				systems/fcs/control-mode == 26
				systems/fcs/control-mode == 27
				systems/fcs/control-mode == 28
			</test>
		<output>fcs/airfoil-factor-roll-base</output>
		</switch>

    <fcs_function name="fcs/airfoil-factor-roll">
    <function>
	<product>
		<property>fcs/airfoil-factor-roll-base</property>
		<property>systems/fcs/actuator-stall-factor</property>
	</product>
    </function>
    </fcs_function>

    <pure_gain name="Roll damper">
	<input>velocities/p-rad_sec</input>
	<gain>-1.0</gain>
	<output>fcs/roll-damper-cmd-norm</output>
   </pure_gain>
  
   <fcs_function name="Beta dot damper">
	<function>
		<max>
		<min>
		<product>
			<property>aero/beta-rad</property>
			<value>-250.0</value>
			<table>
        			<independentVar lookup="row">velocities/mach</independentVar>
        			<tableData>
          			 0.0        0.00
          	 		 5.0        0.00
	 	  		10.0	    1.00
		   		20.0	    1.00
        			</tableData>
      			</table>
		</product>
		<value>1.0</value>
		</min>
		<value>-1.0</value>
		</max>
	</function>
	<output>fcs/beta-dot-damper-cmd-norm</output>
   </fcs_function>

   <switch name="fcs/ap/auto-aileron-cmd-norm">
	<default value="0.0"/>
	<test  value="systems/ap/taem/taem-controller-aileron-cmd-norm">
		systems/ap/auto-taem-active == 1
	</test>
	<test  value="systems/ap/entry/entry-controller-aileron-cmd-norm">
		systems/ap/auto-entry-active == 1
	</test>
	<test  value="systems/ap/grtls/roll-cmd">
		systems/ap/auto-grtls-active == 1
	</test>
   </switch>

   <switch name="fcs/ap/auto-roll-active">
	<default value="0.0"/>
	<test logic="AND" value="1.0">
		systems/ap/auto-taem-active == 1
		systems/ap/automatic-roll-control == 1
	</test>
	<test logic="AND" value="1.0">
		systems/ap/auto-entry-active == 1
		systems/ap/automatic-roll-control == 1
	</test>
	<test logic="AND" value="1.0">
		systems/ap/auto-grtls-active == 1
		systems/ap/automatic-roll-control == 1
	</test>
   </switch>

   <fcs_function name="fcs/aileron-ap-cmd-merge">
   <function>
	<sum>
		<product>
			<difference>
				<value>1</value>
				<property>fcs/ap/auto-roll-active</property>
			</difference>
			<property>fcs/aileron-cmd-norm-css</property>
		</product>
		<product>
			<property>fcs/ap/auto-roll-active</property>
			<property>fcs/ap/auto-aileron-cmd-norm</property>
		</product>
	</sum>
   </function>
   </fcs_function>


   <fcs_function name="fcs/roll-error">
	 <function>
		<product>
	 	<difference>
			<property>velocities/p-rad_sec</property>
			<product>
				<property>fcs/aileron-ap-cmd-merge</property>
				<value>0.5</value>
			</product>
		</difference>
		<value>-1</value>
		</product>
	</function>
  </fcs_function>

  <deadband name="fcs/roll-PID-trigger">
	<input>fcs/roll-error</input>
	<width>0.2</width>
  </deadband>

  <pid name="fcs/roll-controller">
	<input>fcs/roll-error</input>
	<kp> 20.0 </kp>
	<ki> 3.0 </ki>
	<kd> 15.0</kd>
	<trigger>fcs/roll-PID-trigger</trigger>
	<clipto>
		<min> -1.0 </min>
        	<max>  1.0 </max>
	</clipto>
	<output>fcs/roll-controller-out</output>
  </pid>

  <fcs_function name="fcs/roll-command">
  <function>
	<sum>
	<product>
		<property>systems/fcs/airfoil-rate-control</property>
		<property>fcs/roll-controller</property>
	</product>
	<product>
		<difference>
			<value>1.0</value>
			<property>systems/fcs/airfoil-rate-control</property>	
		</difference>
		<sum>
		<property>fcs/aileron-cmd-norm-css</property>
		<property>fcs/roll-damper-cmd-norm</property>
		</sum>
	</product>
	</sum>
  </function>
  </fcs_function>
  

   <summer name="Roll Trim Sum">
      <input>fcs/roll-command</input>
      <input>fcs/roll-trim-cmd-norm</input>
      <input>fcs/beta-dot-damper-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-command</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-command</output>
   </aerosurface_scale>

   <!-- Priority rate limiting dependent on number of available hydraulics systems -->

   <kinematic name="Left Aileron Movement PRL 3 and 2">
	<input>fcs/left-aileron-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>2.86</time>
		</setting>
		</traverse>
	<output>fcs/left-aileron-pos-prl32-rad</output>
   </kinematic>

   <kinematic name="Left Aileron Movement PRL 1">
	<input>fcs/left-aileron-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>4.11</time>
		</setting>
		</traverse>
	<output>fcs/left-aileron-pos-prl1-rad</output>
   </kinematic>

   <switch name="Priority rate limiting left aileron">
			<default value="0.0"/>
			<test logic="OR" value="fcs/left-aileron-pos-prl32-rad">
				systems/apu/number-systems-pressurized == 3
				systems/apu/number-systems-pressurized == 2
			</test>
			<test value="fcs/left-aileron-pos-prl1-rad">
				systems/apu/number-systems-pressurized == 1
			</test>
	<output>fcs/left-aileron-pos-prl-rad</output>
   </switch>

   <kinematic name="Right Aileron Movement PRL 3 and 2">
	<input>fcs/right-aileron-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>2.86</time>
		</setting>
		</traverse>
	<output>fcs/right-aileron-pos-prl32-rad</output>
   </kinematic>

   <kinematic name="Right Aileron Movement PRL 1">
	<input>fcs/right-aileron-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>4.11</time>
		</setting>
		</traverse>
	<output>fcs/right-aileron-pos-prl1-rad</output>
   </kinematic>

   <switch name="Priority rate limiting right aileron">
			<default value="0.0"/>
			<test logic="OR" value="fcs/right-aileron-pos-prl32-rad">
				systems/apu/number-systems-pressurized == 3
				systems/apu/number-systems-pressurized == 2
			</test>
			<test value="fcs/right-aileron-pos-prl1-rad">
				systems/apu/number-systems-pressurized == 1
			</test>
	<output>fcs/right-aileron-pos-prl-rad</output>
   </switch>

  <pure_gain name="Actual Left Aileron Motion">
	<!--<input>fcs/left-aileron-pos-rad-command</input>-->
	<input>fcs/left-aileron-pos-prl-rad</input>
	<gain>fcs/airfoil-factor-roll</gain>
	<output>fcs/left-aileron-pos-rad</output>
   </pure_gain>

  <pure_gain name="Actual Right Aileron Motion">
	<!--<input>fcs/right-aileron-pos-rad-command</input>-->
	<input>fcs/right-aileron-pos-prl-rad</input>
	<gain>fcs/airfoil-factor-roll</gain>
	<output>fcs/right-aileron-pos-rad</output>
   </pure_gain>

   <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">

  <switch name="Disable airfoil yaw if thrust vectoring is used">
			<default value="1.0"/>
			<test logic="OR" value="0.0">
				systems/fcs/control-mode == 0
				systems/fcs/control-mode == 10
				systems/fcs/control-mode == 11
				systems/fcs/control-mode == 1
				systems/fcs/control-mode == 2
				systems/fcs/control-mode == 3
				systems/fcs/control-mode == 20
				systems/fcs/control-mode == 21
				systems/fcs/control-mode == 22
				systems/fcs/control-mode == 23
				systems/fcs/control-mode == 25
				systems/fcs/control-mode == 26
				systems/fcs/control-mode == 27
				systems/fcs/control-mode == 28
			</test>
		<output>fcs/airfoil-factor-yaw-base</output>
    </switch>

   <fcs_function name="fcs/airfoil-factor-yaw">
   <function>
	<product>
		<property>fcs/airfoil-factor-yaw-base</property>
		<property>systems/fcs/actuator-stall-factor</property>
	</product>
   </function>
   </fcs_function>

   <switch name="Disable automatic rudder in orbit">
			<default value="1.0"/>
			<test  logic="OR" value="0.0">
				velocities/mach GT 10.0
			</test>
		<output>fcs/automatic-rudder</output>
   </switch>

   <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm-css</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </clipto>
   </summer>

   

   <!-- ultimately rudder input is supposed to be a bias of the error - not in yet -->
   <fcs_function name="fcs/beta-error-rad">
	 <function>
		<product>
	 	<difference>
			<product>
				<property>aero/beta-rad</property>
				<value>-1.0</value>
			</product>
			<value>0.0</value>
		</difference>
		</product>
	</function>
  </fcs_function>

  <pid name="fcs/beta-controller">
	<input>fcs/beta-error-rad</input>
	<kp> 10.0 </kp>
	<ki> 0.0 </ki>
	<kd> 10.0</kd>
	<clipto>
		<min> -0.35 </min>
        	<max>  0.35 </max>
	</clipto>
  </pid>

  <fcs_function name="fcs/beta-controller-corrected">
      <function>
      <product>
      <property>fcs/beta-controller</property>
      <table>
        <independentVar lookup="row">velocities/mach</independentVar>
        <tableData>
           1.0    1.0
           2.0	  2.0
	   4.0	  3.0	     
        </tableData>
      </table>
      <property>fcs/automatic-rudder</property>
      </product>
      </function>
   </fcs_function>



   <summer name="Rudder Sum">
      <input>fcs/rudder-command-sum</input>
      <input>fcs/beta-controller-corrected</input>
      <!--<input>fcs/yaw-damper-final</input>-->
      <clipto>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </clipto>
      <output>fcs/rudder-pos-rad-command</output>
   </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-command</output>
   </aerosurface_scale>-->

  <kinematic name="Rudder Movement">
	<input>fcs/rudder-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>1.0</time>
		</setting>
		</traverse>
	<output>fcs/rudder-pos-rad-motion</output>
   </kinematic>

   <!-- Priority rate limiting dependent on number of available hydraulics systems -->

   <kinematic name="Rudder Movement PRL 3">
	<input>fcs/rudder-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>4.08</time>
		</setting>
		</traverse>
	<output>fcs/rudder-pos-prl3-rad</output>
   </kinematic>

   <kinematic name="Rudder Movement PRL 2">
	<input>fcs/rudder-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>4.76</time>
		</setting>
		</traverse>
	<output>fcs/rudder-pos-prl2-rad</output>
   </kinematic>

   <kinematic name="Rudder Movement PRL 1">
	<input>fcs/rudder-pos-rad-command</input>
	<traverse>
		<setting>
			<position>-1.0</position>
			<time>0</time>
		</setting>
		<setting>
			<position>1.0</position>
			<time>8.16</time>
		</setting>
		</traverse>
	<output>fcs/rudder-pos-prl1-rad</output>
   </kinematic>

   <switch name="Rudder Priority Rate Limiting">
			<default value="0.0"/>
			<test value="fcs/rudder-pos-prl3-rad">
				systems/apu/number-systems-pressurized == 3
			</test>
			<test value="fcs/rudder-pos-prl2-rad">
				systems/apu/number-systems-pressurized == 2
			</test>
			<test value="fcs/rudder-pos-prl1-rad">
				systems/apu/number-systems-pressurized == 1
			</test>
	<output>fcs/rudder-pos-prl-rad</output>
   </switch>

   <!-- this is a bit hacky - priority limiting doesn't deal correctly with init yaw deviation -->
   <!-- so we allow on init a faster airfoil movement to handle a stable state to the controls -->
   <!-- once the actual PRL simulation starts -->

   <switch name="Rudder Init">
			<default value="fcs/rudder-pos-prl-rad"/>
			<test value="fcs/rudder-pos-rad-motion">
				systems/apu/init-hydraulics-on == 1
			</test>
   <output>fcs/rudder-pos-prl-rad</output>
   </switch>


   <pure_gain name="Actual Rudder Motion">
	<!--<input>fcs/rudder-pos-rad-command</input>-->
 	<input>fcs/rudder-pos-prl-rad</input>
	<gain>fcs/airfoil-factor-yaw</gain>
	<output>fcs/rudder-pos-rad</output>
   </pure_gain>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad-command</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1.0 </min>
        <max>  1.0 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>
  </channel>

  <channel name="Inboard elevon left">
 	<summer name="Inboard elevon left sum">
      		<input>fcs/elevator-pos-deg</input>
      		<input>fcs/left-aileron-pos-deg</input>
      		<clipto>
        		<min> -40.0 </min>
        		<max>  25.0 </max>
      		</clipto>
      		<output>fcs/inboard-elevon-left-pos-deg</output>
   	</summer>
  </channel>

  <channel name="Outboard elevon left">
 	<summer name="Outboard elevon left sum">
      		<input>fcs/elevator-pos-deg</input>
      		<input>fcs/left-aileron-pos-deg</input>
      		<clipto>
        		<min> -40.0 </min>
        		<max>  25.0 </max>
      		</clipto>
      		<output>fcs/outboard-elevon-left-pos-deg</output>
   	</summer>
  </channel>

  <channel name="Inboard elevon right">
 	<summer name="Inboard elevon right sum">
      		<input>fcs/elevator-pos-deg</input>
      		<input>fcs/right-aileron-pos-deg</input>
      		<clipto>
        		<min> -40.0 </min>
        		<max>  25.0 </max>
      		</clipto>
      		<output>fcs/inboard-elevon-right-pos-deg</output>
   	</summer>
  </channel>

  <channel name="Outboard elevon right">
 	<summer name="Outboard elevon right sum">
      		<input>fcs/elevator-pos-deg</input>
      		<input>fcs/right-aileron-pos-deg</input>
      		<clipto>
        		<min> -40.0 </min>
        		<max>  25.0 </max>
      		</clipto>
      		<output>fcs/outboard-elevon-right-pos-deg</output>
   	</summer>
  </channel>


  <channel name="Landing Gear">

   <fcs_function name="gear/gear-filtered-cmd-norm">
	<function>
	<product>	
		<property>gear/gear-cmd-norm</property>
		<property>systems/landing/landing-gear-arm-cmd</property>
	</product>
	</function>
   </fcs_function>	

   <kinematic name="Gear Control">
     <input>gear/gear-filtered-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     1.5 </time>
       </setting>
     </traverse>
     <output>gear/gear-pos-norm</output>
   </kinematic>

  </channel>

  <channel name="Speedbrake">
   <kinematic name="Speedbrake Control PRL 2 and 3">
     <input>/controls/shuttle/speedbrake</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     8.08 </time>
       </setting>
     </traverse>
     <output>fcs/speedbrake-pos-prl23-norm</output>
   </kinematic>

   <kinematic name="Speedbrake Control PRL 1">
     <input>/controls/shuttle/speedbrake</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     9.01 </time>
       </setting>
     </traverse>
     <output>fcs/speedbrake-pos-prl1-norm</output>
   </kinematic>

   <switch name="Speedbrake Priority Rate Limiting">
	<default value="0.0"/>
	<test logic="OR" value="fcs/speedbrake-pos-prl23-norm">
		systems/apu/number-systems-pressurized == 3
		systems/apu/number-systems-pressurized == 2
	</test>
	<test value="fcs/speedbrake-pos-prl1-norm">
		systems/apu/number-systems-pressurized == 1
	</test>
	<output>fcs/speedbrake-pos-norm</output>
   </switch>

  </channel>
 

  <channel name="Bodyflap">
   <kinematic name="Bodyflap Control">
     <input>/controls/shuttle/bodyflap-pos-rad</input>
     <traverse>
	<setting>
          <position> -1.0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1.0 </position>
          <time>     9 </time>
       </setting>
     </traverse>
     <output>fcs/bodyflap-pos-rad</output>
   </kinematic>

  </channel>
 
 <!-- Parachute -->
  <channel name="chute">
   <fcs_function name="fcs/parachute_reef_pos_norm">
    <function>
     <product>
      <value>0.5</value>
      <property>/controls/shuttle/parachute</property>      
     </product>
    </function>
    <clipto>
     <min>0.0</min>
     <max>1.0</max>
    </clipto>
   </fcs_function>

  <pure_gain name="metrics/chute-sqft">
    <input>fcs/parachute_reef_pos_norm</input>
    <gain> 600.0 </gain> <!-- Area of braking chute = ca 650-->
   </pure_gain>
  </channel>
<!-- Parachute -->
  
  
<!--  <channel name="Accelerometer">

<accelerometer name="accelerations/translational-acc-1">
  <location unit="M">
    <x> 2.7 </x>
    <y> 0.0 </y>
    <z>-2.7 </z>
  </location>
  <axis>X</axis>
  <drift_rate> 0.0</drift_rate>
  <output>accelerations/ax-trans-ft_sec2</output>
</accelerometer>

<accelerometer name="accelerations/translational-acc-2">
  <location unit="M">
    <x> 2.7 </x>
    <y> 0.0 </y>
    <z>-2.7 </z>
  </location>
  <axis>Y</axis>
  <drift_rate> 0.0</drift_rate>
  <output>accelerations/ay-trans-ft_sec2</output>
</accelerometer>

<accelerometer name="accelerations/translational-acc-3">
  <location unit="M">
    <x> 2.7 </x>
    <y> 0.0 </y>
    <z>-2.7 </z>
  </location>
  <axis>Z</axis>
  <drift_rate> 0.0</drift_rate>
  <output>accelerations/az-trans-ft_sec2</output>
</accelerometer>

  </channel>-->


 </flight_control>

<!-- aerodynamical data is taken from 'Aerodynamical design of the Space Shuttle Orbiter', Bornemann and Surber -->
<!-- Rockwell International Space Systems Group -->
<!-- and 'Entry Dynamics of Space Shuttle Orbiter With Longitudinal Stability and Control -->
<!-- Uncertainties at Supersonic and Hypersonic Speeds', Stone and Powell, NASA -->
<!-- except for lift and drag which is a 2-dim parametrization of wind tunnel data by Dilao and Fonsecq -->

<!-- aero data used for launch stack is from 'Space shuttle: Determination of the aerodynamic -->
<!-- interference between the space shuttle orbiter, external tank, and solid rocket booster on -->
<!-- a 0.004 scale ascent configuration', Ramsey, Buchholz, Allen, Dehart, NASA -->


 <aerodynamics>
  

  <function name="aero/coefficient/K">
	<product>
		<value>0.5</value>
		<sum>	
		<value>1.0</value>
			<pow>
			<abs>
				<difference>	
				<value>1.0</value>
				<pow>
					<quotient>	
					<property>velocities/mach</property>
					<value>1.25</value>
					</quotient>
					<value>2.0</value>
				</pow>
				</difference>
			</abs>
			<value>0.5</value>
			</pow>
		</sum>
	</product>
  </function>

  <function name="aero/coefficient/CLtest">
	<product>
	<sum>
			<value>-0.053</value>
			<product>
				<value>2.73</value>
				<property>aero/alpha-rad</property>			
			</product>
			<product>
				<value>-1.55</value>
				<pow>
					<property>aero/alpha-rad</property>
					<value>2.0</value>
				</pow>
			</product>
		</sum>
		<pow>
		<property>aero/coefficient/K</property>
		<sum>
			<value>-1.01</value>
			<product>
				<property>aero/alpha-rad</property>
				<value>1.1</value>
			</product>
		</sum>
		</pow>
	</product> 

  </function>


 
  <function name="aero/coefficient/CDtest">
  <product>
        	
    		<sum>
			<value>0.01</value>
			<product>
				<value>0.028</value>
				<pow>
					<property>velocities/mach</property>
					<value>1.4</value>
				</pow>			
			</product>
			<product>
				<value>1.79</value>
				<pow>
					<property>aero/alpha-rad</property>
					<value>2.0</value>
				</pow>
			</product>
		</sum>
		<pow>
		<property>aero/coefficient/K</property>
		<sum>
			<value>-1.4</value>
			<product>
				<property>aero/alpha-rad</property>
				<value>1.5</value>
			</product>
		</sum>
		</pow>
		<difference>
			<value>1.0</value>
			<product>
				<value>0.28</value>
				<property>/sim/config/shuttle/approach-and-landing-test-config</property>
			</product>
		</difference>
	</product> 
</function>

 <function name="aero/coefficient/GS">
	<quotient>
		<property>aero/coefficient/CLtest</property>
		<property>aero/coefficient/CDtest</property>
	</quotient>
 </function>

  <function name="aero/coefficient/CN">
  <description>Normal force coefficient</description>
	<sum>
		<product>
			<property>aero/coefficient/CLtest</property>
			<cos>
				<property>aero/alpha-rad</property>			
			</cos>
		</product>
		<product>
			<property>aero/coefficient/CDtest</property>
			<sin>
				<property>aero/alpha-rad</property>			
			</sin>
		</product>
	</sum>
  </function>


 <function name="aero/coefficient/ground_effect">
      <table>
        <independentVar lookup="row">position/h-agl-ft</independentVar>
         <tableData>
           13.0		1.25
	   20.0		1.10
	   30.0		1.05
	   40.0		1.00
         </tableData>
      </table>
   </function>

  <axis name="LIFT">
	<function name="aero/coefficient/CL">
	<description>2d parametrization of the lift as function of AoA and Mach number</description>
	<product>
        	<property>aero/qbar-psf</property>
         	<property>metrics/Sw-sqft</property>
    		<sum>
			<value>-0.053</value>
			<product>
				<value>2.73</value>
				<property>aero/alpha-rad</property>			
			</product>
			<product>
				<value>-1.55</value>
				<pow>
					<property>aero/alpha-rad</property>
					<value>2.0</value>
				</pow>
			</product>
		</sum>
		<pow>
		<property>aero/coefficient/K</property>
		<sum>
			<value>-1.01</value>
			<product>
				<property>aero/alpha-rad</property>
				<value>1.1</value>
			</product>
		</sum>
		</pow>
	<property>systems/failures/aero-structure-condition</property>
	<property>aero/coefficient/ground_effect</property>
	</product> 
	</function>   
  </axis>

  <axis name="DRAG">

	<function name="aero/coefficient/CD">
	<description>2d parametrization of the drag as function of AoA and Mach number</description>
	<product>
        	<property>aero/qbar-psf</property>
         	<property>metrics/Sw-sqft</property>
    		<sum>
			<value>0.01</value>
			<product>
				<value>0.028</value>
				<pow>
					<property>velocities/mach</property>
					<value>1.4</value>
				</pow>			
			</product>
			<product>
				<value>1.79</value>
				<pow>
					<property>aero/alpha-rad</property>
					<value>2.0</value>
				</pow>
			</product>
		</sum>
		<pow>
		<property>aero/coefficient/K</property>
		<sum>
			<value>-1.4</value>
			<product>
				<property>aero/alpha-rad</property>
				<value>1.5</value>
			</product>
		</sum>
		</pow>
		<difference>
			<value>1.0</value>
			<product>
				<value>0.28</value>
				<property>/sim/config/shuttle/approach-and-landing-test-config</property>
			</product>
		</difference>
	</product> 
	</function>   

	<!-- gear drag is from 'Aerodynamical Design of the Space Shuttle Orbiter -->
	<function name="aero/coefficient/CDgear">
        	<description>Drag of landing gear</description>
         	<product>
           		<property>aero/qbar-psf</property>
           		<property>metrics/Sw-sqft</property>
           		<property>gear/gear-pos-norm</property>
           		<value>0.0215</value>
         	</product>
   	</function>

	<!-- crew manual mentions that gear drag is 60% of speedbrake effect -->
	<!-- almost certainly needs Mach number dependence -->
    	<function name="aero/coefficient/CDSb">
       	<description>Drag of the tail speedbrake</description>
         	<product>
           		<property>aero/qbar-psf</property>
           		<property>metrics/Sw-sqft</property>
           		<property>fcs/speedbrake-pos-norm</property>
           		<value>0.0344</value>
         	</product>
    	</function>

	<function name="aero/coefficient/CDpc">
    	<description>Drag of braking parachute</description>
    		<product>
     			<property>aero/qbar-psf</property>
     			<property>metrics/chute-sqft</property>    
     			<property>fcs/parachute_reef_pos_norm</property>
     			<value>0.25</value>
			<property>systems/failures/drag-chute-condition</property>
    			</product>
   	</function>


  </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>-->
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                        2.48	-0.81
			2.99	-0.75
			3.51	-0.66
			3.98	-0.60
			4.47	-0.54
			9.98	-0.38
                  </tableData>
         </table>
       </product>
    </function>

   <function name="aero/coefficient/CYdr">
       <description>Side_force_due_to_rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/rudder-pos-rad</property>
	   <property>systems/failures/airfoils-yaw-condition</property>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                        2.48	0.064
			2.99	0.049
			3.51	0.037
			3.98	0.031
			4.47	0.027
			9.98	0.0
                  </tableData>
         </table>
       </product>
    </function>

   <function name="aero/coefficient/CYda">
       <description>Side_force_due_to_aileron</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/left-aileron-pos-rad</property>
	   <property>systems/failures/airfoils-roll-condition</property>
	   <property>systems/apu/hyd-pressure-available</property>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                        2.48	0.02038
			2.99	0.02241
			3.51	0.01873
			3.98	0.01375
			4.47	0.01501
			9.98	0.02215
                  </tableData>
         </table>
       </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>
	   <property>aero/orbiter-config</property>
	   <value>57.2975</value>
	   <sum>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                          0.4	-0.0025
			  0.6	-0.0022
			  0.8	-0.002
			  1.0	-0.0022
			  2.0	-0.0015
			  4.0	-0.0015
			  6.0	-0.0016
			  10.0	-0.0018
			  20.0	-0.0018     
                  </tableData>
         </table>
	<table>
                  <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
		  <independentVar lookup="column">velocities/mach</independentVar>
                  <tableData>
                       		0.6		3.0
			-40.0	0.0015		0.0005
			-30.0	0.0009		0.00035
			-10.0	0.00025		0.0001
			0.0	0.0		0.0	
			10.0	0.0002		-0.00015
			20.0	0.0004		-0.0002
                  </tableData>
         </table>
	 </sum>
           <!--<value>-0.1</value>-->
       </product>
    </function>

   <function name="aero/coefficient/Clb-launch">
       <description>Roll_moment_due_to_beta_launch_vehicle</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
	   <property>aero/launch-config</property>
	   <!--<value>-0.05</value>-->
	   <value>57.2975</value>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                   	0.5	-0.0062
			1.0	-0.008
			1.5	-0.008
			3.0	-0.004
			5.0	-0.0025	   
                  </tableData>
         </table>
       </product>
    </function>

    <!-- table 2 from 'Separate Surface Control' -->

    <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>
	   <property>aero/orbiter-config</property>
            <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                        2.48	-0.2358
			2.99	-0.2331
			3.51	-0.2324
			3.98	-0.2253
			4.47	-0.2094
			9.98	-0.2332 
                  </tableData>
         </table>
       </product>
    </function>

    <function name="aero/coefficient/Clp-launch">
       <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>
	   <property>aero/launch-config</property>
           <!--<value>-0.4</value>-->
	   <value>-1.4</value>-->
       </product>
    </function>

    <!-- table 2 from 'Separate Surface Control' -->

    <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>-->
		<table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                        2.48	0.08294
			2.99	0.06157
			3.51	0.05322
			3.98	0.04442
			4.47	0.04321
			9.98	0.05337
                  </tableData>
         </table>
       </product>
    </function>


    <!-- base coefficients and dependence on elevator deflection from 'Aerodynamical design...'-->

    <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>
	  <property>systems/failures/airfoils-roll-condition</property>
	  <property>systems/apu/hyd-pressure-available</property>
 	  <value>57.2975</value>
	   <product>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                          0.4	0.0042
			  0.6	0.0042
			  0.8	0.0039
			  1.0	0.0027
			  2.0	0.001
			  4.0	0.0008
			  6.0	0.001
			  10.0	0.0014
			  20.0	0.0014     
                  </tableData>
         </table>
	<table>
                  <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
		  <independentVar lookup="column">velocities/mach</independentVar>
                  <tableData>
                       		0.6		3.0
			-40	0.119		0.250
			-30	0.119		0.313
			-20	0.214		0.563
			-10	0.833		0.750
			0.0	1.000		1.000
			10.0	0.952		1.375
			20.0	0.881		1.875
		</tableData>
	</table>
  	</product>
 	<!--<table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <independentVar lookup="column">position/h-sl-ft</independentVar>
                  <tableData>
                                0.0000	80000.0000
                              0.0000	0.0500	0.0500
                              0.4000	0.0700	0.0500
                              0.6000	0.0800	0.0500
                              1.0000	0.1100	0.0500
                              1.4000	0.0800	0.0600
                              1.6000	0.0700	0.0600
                              2.4000	0.0600	0.0500
                              6.0000	0.0300	0.0200
                   </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>
	   <property>systems/failures/airfoils-yaw-condition</property>
	   <property>systems/apu/hyd-pressure-available</property>
	   <value>57.2975</value>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                          0.4	0.0008
			  0.6	0.0008
			  0.8	0.0009
			  1.0	0.001
			  2.0	0.0005
			  4.0	0.00025
			  6.0	0.0001
			  10.0	0.0
			  20.0	0.0    
                  </tableData>
         </table>
           <!--<value>0.01</value>-->
       </product>
    </function>

    

  </axis>

  <axis name="PITCH">

   <!-- Date points from 'Aerodynamical Design of the Space Shuttle Orbiter' -->
   <!-- tables extrapolated to cover full range of elevator movements -->


   <function name ="aero/coefficient/Cm">
   <description>Pitch_moment_as_function_of_alpha_elevator_and_Mach_number</description>
   <product>
   	<property>aero/qbar-psf</property>
   	<property>metrics/Sw-sqft</property>
       	<property>metrics/cbarw-ft</property>
	<property>aero/orbiter-config</property>
	<table>
		<independentVar lookup="row">aero/coefficient/CN</independentVar>
		<independentVar lookup="column">fcs/elevator-pos-deg</independentVar>
		<independentVar lookup="table">velocities/mach</independentVar>
		<tableData breakPoint="0.6">
			-40.0	0.0	5.0	10.0	25.0
		0.0	0.4	0.05	0.0	-0.05	-0.2
		0.2	0.38	0.04	0.0	-0.05	-0.2
		0.4	0.38	0.04	-0.005	-0.055	-0.21
		0.7	0.37	0.03	-0.01	-0.06	-0.22
		1.1	0.35	0.01	-0.04	-0.08	-0.24
		1.3	0.43	0.07	0.02	-0.03	-0.18
		</tableData>
		<tableData breakPoint="1.2">
			-40.0	-10.0	0.0	10.0	25.0
		0.0	0.4	0.15	0.08	0.02	-0.08
		0.2	0.35	0.11	0.05	-0.02	-0.12
		0.4	0.3	0.07	0.005	-0.06	-0.16
		0.7	0.22	0.025	-0.03	-0.09	-0.19
		1.1	0.15	0.005	-0.05	-0.13	-0.23
		1.3	0.23	0.025	-0.045	-0.12	-0.22
		</tableData>
		<tableData breakPoint="5.0">
			-40.0	-35.0	0.0	10.0	25.0
		0.0	0.017	0.015	0.0	-0.005	-0.012
		0.2	0.017	0.015	0.0	-0.01	-0.024
		0.4	0.017	0.015	0.0	-0.02	-0.047
		0.7	0.02	0.015	-0.02	-0.06	-0.12
		1.1	0.02	0.014	-0.04	-0.1	-0.2
		1.3	0.02	0.014	-0.05	-0.125	-0.26
		</tableData>
		<tableData breakPoint="10.0">
			-40.0	-35.0	0.0	10.0	25.0
		0.0	0.001	0.0	-0.01	-0.025	-0.04
		0.2	0.012	0.01	-0.01	-0.025	-0.05
		0.4	0.022	0.02	0.0	-0.03	-0.065
		0.7	0.035	0.03	-0.01	-0.04	-0.09
		1.1	0.05	0.04	-0.02	-0.075	-0.17
		1.3	0.05	0.04	-0.03	-0.1	-0.2
		</tableData>
	</table>
   </product>
   </function>

   <!-- Date points from 'Entry dynamics ...', extrapolated to Mach 10 -->

  <function name ="aero/coefficient/CmSB">
   <description>Pitching_moment_due_to_speedbrake</description>
   <product>
   	<property>aero/qbar-psf</property>
   	<property>metrics/Sw-sqft</property>
       	<property>metrics/cbarw-ft</property>
        <property>fcs/speedbrake-pos-norm</property>
	<table>
	<independentVar lookup="row">aero/alpha-deg</independentVar>
	<independentVar lookup="column">velocities/mach</independentVar>
		<tableData>
			1.5	3.0	5.0	10.0
		-10.0	0.046	0.031	0.025	0.0125
		10.0	0.030	0.015	0.0094	0.0043
		30.0	0.022	0.0077	0.0028	0.0013
		50.0	0.015	0.0005	0.0	0.0
		</tableData>
	  </table>
   </product>
  </function>

  <!-- Date points from 'Entry dynamics ...', extrapolated to Mach 10 -->
  <!-- normalization is unusual - the table is for -11.5 deg deflection --> 

  <function name ="aero/coefficient/CmBF">
   <description>Pitching_moment_due_to_Body_Flap</description>
   <product>
   	<property>aero/qbar-psf</property>
   	<property>metrics/Sw-sqft</property>
       	<property>metrics/cbarw-ft</property>
        <property>fcs/bodyflap-pos-rad</property>
	<value>-5.0</value>
	<table>
	<independentVar lookup="row">aero/alpha-deg</independentVar>
	<independentVar lookup="column">velocities/mach</independentVar>
		<tableData>
			1.5	3.0	5.0	10.0
		-10.0	0.005	0.0	0.0	0.0
		20.0	0.01	0.005	0.002	0.0012
		30.0	0.017	0.01	0.006	0.0032
		50.0	0.038	0.03	0.02	0.012
		</tableData>
	  </table>
   </product>
  </function>



    <!-- Data from "Determination of the aerodynamic interference between the space shuttle orbiter, -->
    <!-- external tank, and solid rocket booster" using O/T5/S1 config-->

    <function name="aero/coefficient/Cmalpha-launch">
       <description>Pitch_moment_due_to_alpha_launch_vehicle</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/alpha-rad</property>
	   <property>aero/launch-config</property>
	   <!--<value>-0.05</value>-->
	   <value>57.2975</value>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
		   	0.5	-0.0165 
		   	1.0	-0.022
			1.5	-0.0142
			2.0	-0.0085
			3.0	-0.006
			5.0	-0.0055 
                  </tableData>
         </table>
       </product>
    </function>

    <function name="aero/coefficient/Cmde-launch">
       <description>Pitch_moment_due_to_elevator_launch_vehicle</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
	  <property>aero/launch-config</property>
	  <property>systems/failures/airfoils-pitch-condition</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>-->
	  <value>-70</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>
	   <property>aero/orbiter-config</property>
 	   <value>57.2975</value>
	   <sum>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                          0.4	0.015
			  0.6	0.017
			  0.8	0.02
			  1.0	0.019
			  2.0	-0.0005
			  4.0	-0.001
			  6.0	-0.00125
			  10.0	-0.0011
			  20.0	-0.0011    
                  </tableData>
         </table>
	 <table>
                  <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
		  <independentVar lookup="column">velocities/mach</independentVar>
                  <tableData>
                       		0.6		3.0
			-40.0	-0.0013		0.0003
			-30.0	-0.001		0.0002
			-20.0	-0.0007		0.0001
			-10.0	-0.0004		0.00005
			0.0	0.0		0.0	
			10.0	0.0004		-0.00005
			20.0	0.0001		-0.00008
                  </tableData>
         </table>
	 </sum>
           <!--<value>0.12</value>-->
       </product>
    </function>


    <function name="aero/coefficient/Cnb-launch">
       <description>Yaw_moment_due_to_beta_launch_vehicle</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
	   <property>aero/launch-config</property>
	   <value>57.2975</value>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                  	0.5	0.016
			1.0	0.022
			1.5	0.017
			3.0	0.010
			5.0	0.008
                  </tableData>
         </table>
	   <!--<value>0.12</value>-->
	</product>
   </function>

    <!-- table 2 from 'Separate Surface Control' -->
    <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>
	   <property>aero/orbiter-config</property>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                   	2.48	-0.594
			2.99	-0.68
			3.15	-0.717
			3.98	-0.676
			4.47	-0.655
			9.98	-0.19	   
                  </tableData>
         </table>
           <!--<value>-0.15</value>-->
       </product>
    </function>

    <function name="aero/coefficient/Cnr-launch">
       <description>Yaw_moment_due_to_yaw_rate_launch_vehicle</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>
	   <property>aero/launch-config</property>
           <value>-0.15</value>
       </product>
    </function>

     <!-- table 2 from 'Separate Surface Control' -->
    <function name="aero/coefficient/Cnp">
       <description>Yaw_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>
	   <property>aero/orbiter-config</property>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                   	2.48	0.057
			2.99	0.029
			3.15	0.012
			3.98	0.0036
			4.47	-0.0048
			9.98	-0.036	   
                  </tableData>
         </table>
           <!--<value>0.0</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>
	   <property>systems/failures/airfoils-yaw-condition</property>
	   <property>systems/apu/hyd-pressure-available</property>
	   <value>57.2975</value>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                          0.4	-0.0013
			  0.6	-0.0013
			  0.8	-0.00145
			  1.0	-0.0015
			  2.0	-0.00055
			  4.0	-0.00025
			  6.0	-0.00005
			  10.0	0.0
			  20.0	0.0    
                  </tableData>
         </table>
          <!--<value>-0.1</value>-->
       </product>
    </function>

    <!-- this will largely be taken care of by the FCS which uses rudder to get beta to zero-->
    <!-- leave at zero till this is implemented -->
    <function name="aero/coefficient/Cnda">
       <description>Yaw_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>
	   <property>aero/orbiter-config</property>
	   <property>systems/apu/hyd-pressure-available</property>
 	   <value>57.2975</value>
	   <product>
	   <table>
                  <independentVar lookup="row">velocities/mach</independentVar>
                  <tableData>
                          0.4	0.001
			  0.6	0.001
			  0.8	0.0011
			  1.0	0.001
			  2.0	-0.00025
			  4.0	-0.00025
			  6.0	-0.00025
			  10.0	-0.00035
			  20.0	-0.00035    
                  </tableData>
         </table>
	<table>
                  <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
		  <independentVar lookup="column">velocities/mach</independentVar>
                  <tableData>
                       		0.6		3.0
			-40.0	0.454		-0.666
			-30.0	0.909		-0.666
			-20.0	1.500		-0.500
			-10.0	1.363		0.000	
			0.0	1.000		1.000
			10.0	0.363		2.000
			20.0	-0.45		4.000
		</tableData>
	</table>

	 </product>
           <!--<value>0</value>-->
       </product>
    </function>

  
    
  </axis>

 </aerodynamics>

 

 <external_reactions>

  <!-- propellant dump-->

  <force name="propellant_dump" frame="BODY">
    <function>
      <property>systems/mps/propellant-dump-force-lb</property>
    </function>
    <location unit="M">
      <x> 17.0</x>
      <y> 0</y>
      <z>-2.5</z>
    </location>
    <direction>
      <x>1</x>
      <y>0</y>
      <z>0</z>
    </direction>
  </force>

  <!-- hi-load FES exhaust -->

  <force name="fes_exhaust" frame="BODY">
    <function>
      <property>systems/atcs/hiload-fes-exhaust-force-lb</property>
    </function>
    <location unit="M">
      <x> 16.0</x>
      <y>-3.2</y>
      <z>-1.5</z>
    </location>
    <direction>
      <x>0</x>
      <y>1</y>
      <z>0</z>
    </direction>
  </force>

  <!-- Parachute--> 

  <force name="parachute" frame="WIND">
    <function>
      <product>
        <property>aero/qbar-psf</property>
        <property>metrics/chute-sqft</property>
	<property>fcs/parachute_reef_pos_norm</property>
	<property>systems/failures/drag-chute-condition</property>
        <value> 0.3 </value> 
      </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> 


 <system file="orbital_parameters"></system>
 <system file="pointing"></system>
 <system file="apu_hydraulics.xml"></system>
 <system file="electrical_power.xml"></system>
 <system file="atcs.xml"></system>
 <system file="mechanical.xml"></system>
 <system file="rms.xml"></system>
 <system file="mps.xml"></system>
 <system file="rcs_hardware"></system>
 <system file="oms_hardware"></system>
 <system file="rcs_control"></system>
 <system file="eclss"></system>
 <system file="computations"></system>
 <system file="entry_guidance"></system>
 <system file="throttle"></system>
 <system file="thrust_vectoring"></system>
 <system file="failures"></system>
 <system file="cws"></system>
 <system file="ground_effects"></system>
 <system file="autopilot"></system>
 <system file="navigation"></system>
 <system file="light"></system>

</fdm_config>