F4J76-jsbsim.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="F4N" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Aeromatic v 0.9 </author>
  <filecreationdate> now </filecreationdate>
  <version> 0.0 </version>
  <description> Models a F4N. </description>
 </fileheader>

<!--
  File:     F4N.xml
  Inputs:
    name:          F4N
    type:          two-engine transonic/supersonic fighter
    max weight:    61795.0 lb
    wing span:     38.4 ft
    length:        63 ft
    wing area:     530 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     2
    engine type:   turbine
    engine layout: aft fuselage
    yaw damper?    yes
  Outputs:
    wing loading:  116.59 lb/sq-ft
    CL-alpha:      3.6 per radian
    CL-0:          0.08
    CL-max:        1
    CD-0:          0.024
    K:             0.1

-->

 <metrics>
   <wingarea  unit="FT2">  530.00 </wingarea>
   <wingspan  unit="FT" >   38.60 </wingspan>
   <wing_incidence>       0.01745</wing_incidence><!-- radians -->
   <chord     unit="FT" >   16.00 </chord>
   <htailarea unit="FT2">  106.00 </htailarea>
   <htailarm  unit="FT" >   25.20 </htailarm>
   <vtailarea unit="FT2">   95.40 </vtailarea>
   <vtailarm  unit="FT" >   25.20 </vtailarm>
   <location name="AERORP" unit="IN">
     <x>   0.0 </x>
     <y>   0.0 </y>
     <z> -10.0 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x> 151.20 </x>
     <y>   0.00 </y>
     <z>  38.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">     35698 </ixx>
   <iyy unit="SLUG*FT2">    132077 </iyy>
   <izz unit="SLUG*FT2">    124386 </izz>
   <ixy unit="SLUG*FT2">         0 </ixy>
   <ixz unit="SLUG*FT2">         0 </ixz>
   <iyz unit="SLUG*FT2">         0 </iyz>
   <emptywt unit="LBS" >     28000 </emptywt>
   <location name="CG" unit="IN">
     <x> 0 </x>
     <y> 0 </y>
     <z> 0 </z>
   </location>
   <pointmass name="station1"><!-- unused -->
      <weight unit="LBS"> 0 </weight>
      <location name="POINTMASS" unit="IN">
          <x>    6 </x>
          <y> -120 </y>
          <z>  -30 </z>
      </location>
   </pointmass>
   <pointmass name="station2"><!-- unused -->
      <weight unit="LBS"> 0 </weight>
      <location name="POINTMASS" unit="IN">
          <x>   -6 </x>
          <y>  -83 </y>
          <z>  -20 </z>
      </location>
   </pointmass>
   <pointmass name="station3"><!-- empty 600-gal tank -->
      <weight unit="LBS"> 230 </weight>
      <location name="POINTMASS" unit="IN">
          <x>    0 </x>
          <y>    0 </y>
          <z>  -20 </z>
      </location>
   </pointmass>
   <pointmass name="station4"><!-- unused -->
      <weight unit="LBS"> 0 </weight>
      <location name="POINTMASS" unit="IN">
          <x>   -6 </x>
          <y>   83 </y>
          <z>  -20 </z>
      </location>
   </pointmass>
   <pointmass name="station5"><!-- unused -->
      <weight unit="LBS"> 0 </weight>
      <location name="POINTMASS" unit="IN">
          <x>    6 </x>
          <y>  120 </y>
          <z>  -30 </z>
      </location>
   </pointmass>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x>  -261.59 </x>
     <y>   0.00 </y>
     <z> -62.8 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">      18538.50 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  5179.50 </damping_coeff>
   <max_steer unit="DEG"> 75.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 30.22</x>
     <y> -110.00 </y>
     <z> -64.72 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">      41795.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  5359.00 </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="IN">
     <x> 30.22 </x>
     <y>  110.00 </y>
     <z> -64.72 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">      41795.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  5359.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x> 118</x>
     <y> -19.20 </y>
     <z> -18.90 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      61795.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 12359.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 118 </x>
     <y>  19.20 </y>
     <z> -18.90 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      61795.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 12359.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="AFT_FUSELAGE">
    <location unit="IN">
     <x> 600 </x>
     <y>   0 </y>
     <z>   0 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      40000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  8000.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="FWD_FUSELAGE">
    <location unit="IN">
     <x>  50 </x>
     <y>   0 </y>
     <z> -40 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      40000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  8000.00 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="J79-GE-11A">
    <location unit="IN">
      <x> 190 </x>
      <y> -20.00 </y>
      <z>   0.00 </z>
    </location>
    <feed>0</feed>
    <feed>1</feed>
    <feed>2</feed>
    <feed>3</feed>
    <thruster file="direct">
     <location unit="IN">
       <x> 190 </x>
       <y> -20.00 </y>
       <z> -18.9 </z>
     </location>
     <orient unit="DEG">
       <pitch> 1.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="J79-GE-11A">
    <location unit="IN">
      <x> 190 </x>
      <y>  20.00 </y>
      <z>   0.00 </z>
    </location>
    <feed>0</feed>
    <feed>1</feed>
    <feed>2</feed>
    <feed>3</feed>
    <thruster file="direct">
     <location unit="IN">
       <x> 190 </x>
       <y>  20.00 </y>
       <z> -18.9 </z>
     </location>
     <orient unit="DEG">
       <pitch> 1.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <!-- Internal fuel -->
  <tank type="FUEL" number="0">
     <location unit="IN">
       <x>  0   </x>
       <y>  0   </y>
       <z> -6.0 </z>
     </location>
     <capacity unit="LBS"> 13160.00 </capacity>
     <contents unit="LBS"> 13000.00 </contents>
     <standpipe unit="LBS"> 2000.00 </standpipe>
  </tank>

  <!-- Centerline 600 gallon drop tank -->
  <tank type="FUEL" number="1">
     <location unit="IN">
       <x>     0 </x>
       <y>   0.00 </y>
       <z> -20.00 </z>
     </location>
     <capacity unit="LBS"> 3950.00 </capacity>
     <contents unit="LBS"> 1000.00 </contents>
  </tank>

  <!-- Left 370 gallon drop tank -->
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x>      0 </x>
       <y> -139.0 </y>
       <z>  -18.0 </z>
     </location>
     <capacity unit="LBS"> 2440.00 </capacity>
     <contents unit="LBS">    0.00 </contents>
  </tank>

  <!-- Right 370 gallon drop tank -->
  <tank type="FUEL" number="3">
     <location unit="IN">
       <x>      0 </x>
       <y>  139.0 </y>
       <z>  -18.0 </z>
     </location>
     <capacity unit="LBS"> 2440.00 </capacity>
     <contents unit="LBS">    0.00 </contents>
  </tank>

  <dump-rate unit="LBS/MIN"> 2500 </dump-rate>

 </propulsion>

 <system file="holdback"/>
 <system file="hook"/>
 <system file="catapult"/>
 <system file="BLC"/>
 <system file="refuel"/>
 <system file="gear"/> 
 <system file="flaps"/> 
 <system file="speedbrakes"/>
 <system file="FCS-pitch"/>
 <system file="FCS-roll"/>
 <system file="FCS-yaw"/>
 <system file="NWS"/>
 <system file="alpha_buffet"/>
 <system file="dump"/>
 <system file="crash-detect"/>
 <system file="radar"/>
 <system file="armament"/>
 <system file="drag"/>
 <system file="nose_lift"/> 
 <system file="beacon"/>
 <system file="canopy"/>
 <system file="reverser"/>
 <system file="chute"/>
 <system file="wing-fold"/>
 <system file="cat_workaround"/>
 <system file="particles"/>

 <flight_control name="FCS">
 </flight_control>


 <aerodynamics>

    <function name="aero/wing-area">
      <description>Wing-area-including-folding</description>
      <difference>
         <property>metrics/Sw-sqft</property>
         <product>
              <property>metrics/Sw-sqft</property>
              <property>fcs/wing-fold-pos-norm</property>       
              <value>0.4</value> 
         </product>
      </difference>
    </function>

        <function name="aero/function/kCDge">
            <description>Change_in_drag_due_to_ground_effect</description>
            <product>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	0.0480
                          0.1000	0.5150
                          0.1500	0.6290
                          0.2000	0.7090
                          0.3000	0.8150
                          0.4000	0.8820
                          0.5000	0.9280
                          0.6000	0.9620
                          0.7000	0.9880
                          0.8000	1.0000
                      </tableData>
                  </table>
            </product>
        </function>

        <function name="aero/function/kCLge">
            <description>Change_in_lift_due_to_ground_effect</description>
            <product>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	1.2030
                          0.1000	1.1270
                          0.1500	1.0900
                          0.2000	1.0730
                          0.3000	1.0460
                          0.4000	1.0550
                          0.5000	1.0190
                          0.6000	1.0130
                          0.7000	1.0080
                          0.8000	1.0060
                          0.9000	1.0030
                          1.0000	1.0020
                          1.1000	1.0000
                      </tableData>
                  </table>
            </product>
        </function>


  <axis name="LIFT">

    <function name="aero/coefficient/CLalpha">
      <description>Lift_due_to_alpha</description>
      <product>
          <property>aero/qbar-psf</property>
          <property>aero/wing-area</property>
          <property>aero/function/kCLge</property>
          <table>
            <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
            <tableData>
              -3.31  -0.50
              -3.14   0.00
              -2.97   0.90
              -2.79   0.60
              -2.36   1.00
              -0.785 -1.05
              -0.349 -0.60
              -0.26  -1.00
               0.00   0.00
               0.26   1.00
               0.349  0.60
               0.785  1.05
               2.36  -1.00
               2.79  -0.60
               2.97  -0.90
               3.14   0.00
               3.31   0.50 
            </tableData>
          </table>
      </product>
    </function>

    <function name="aero/coefficient/dCLflap">
       <description>Delta_Lift_due_to_flaps</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-norm</property>
           <value> 0.35 </value>
       </product>
    </function>

    <function name="aero/coefficient/dCLsb">
       <description>Delta_Lift_due_to_speedbrake</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>-0.05</value>
       </product>
    </function>

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

    <function name="aero/coefficient/dCLBLC">
       <description>Delta_Lift_due_to_BLC</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>systems/BLC/active</property>
           <property>fcs/flap-pos-norm</property>
           <value> 0.15 </value>
       </product>
    </function>

    <function name="aero/coefficient/buffet">
       <description>Buffet at high alpha</description>
         <product>
           <property>systems/alpha_buffet/sine_wave</property>
           <property>systems/alpha_buffet/strength</property>
         </product>
    </function>

  </axis>

  <axis name="DRAG">

    <function name="aero/coefficient/CD0">
       <description>Basic_drag</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>systems/drag/index</property>
          <property>aero/function/kCDge</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
             -1.57    1.500
             -0.26    0.031
              0.00    0.021
              0.26    0.031
              1.57    1.500
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/CDi">
       <description>Induced_drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value>0.14</value>
         </product>
    </function>

    <function name="aero/coefficient/CDmach">
       <description>Drag_due_to_mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.81      0.000
                1.10      0.018
                1.40      0.009
                2.00      0.004
            </tableData>
          </table>
        </product>
    </function>

    <function name="aero/coefficient/CDflap">
       <description>Drag_due_to_flaps</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-norm</property>
           <value> 0.14</value>
         </product>
    </function>

    <function name="aero/coefficient/CDgear">
       <description>Drag_due_to_gear</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>gear/gear-pos-norm</property>
           <value>0.028</value>
         </product>
    </function>

    <function name="aero/coefficient/CDbc">
       <description>Drag_due_to_braking_chute</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>systems/chute/unfurl-norm</property>
           <value>0.6</value>
         </product>
    </function>

    <function name="aero/coefficient/CDsb">
       <description>Drag_due_to_speedbrakes</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>0.03</value>
         </product>
    </function>

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

    <function name="aero/coefficient/CDde">
       <description>Drag_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <abs><property>fcs/elevator-pos-norm</property></abs>
           <value>0.048</value>
       </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>
       </product>
    </function>

  </axis>

  <axis name="ROLL">

    <function name="aero/coefficient/Clb">
       <description>Roll_moment_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
           <value>-0.05</value>
       </product>
    </function>

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

    <function name="aero/coefficient/Clr">
       <description>Roll_moment_due_to_yaw_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/r-aero-rad_sec</property>
           <value>0.13</value>
       </product>
    </function>

    <function name="aero/coefficient/Clda">
       <description>Roll_moment_due_to_aileron</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/left-aileron-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.120
              2.0    0.040
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/Cldr">
       <description>Roll_moment_due_to_rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>0.005</value>
       </product>
    </function>

  </axis>

  <axis name="PITCH">

    <function name="aero/coefficient/Cmalpha">
       <description>Pitch_moment_due_to_alpha</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/alpha-rad</property>
           <value>-0.3</value>
       </product>
    </function>

    <function name="aero/coefficient/Cmde">
       <description>Pitch_moment_due_to_elevator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -0.70
              2.0     -0.20
            </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>-18</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>-9</value>
       </product>
    </function>

  </axis>

  <axis name="YAW">

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

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

    <function name="aero/coefficient/Cndr">
       <description>Yaw_moment_due_to_rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>-0.08</value>
       </product>
    </function>

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

  </axis>

 </aerodynamics>


 <external_reactions>

  <force name="catapult" frame="LOCAL">
   <location unit="IN">
     <x> -260.0 </x>
     <y>    0.0 </y>
     <z>  -14.0 </z>
   </location>
   <direction>
     <x>   -0.9612617 </x>
     <y>   -0.2756374 </y>
     <z>    0.0 </z>
   </direction>
  </force>

  <force name="holdback" frame="BODY">
   <location unit="IN">
     <x> -250.0 </x>
     <y>    0.0 </y>
     <z>  -30.0 </z>
   </location>
   <direction>
     <x>   -1.0 </x>
     <y>    0.0 </y>
     <z>    0.0 </z>
   </direction>
  </force>

  <force name="hook" frame="BODY">
   <location unit="IN">
     <x>  196.0 </x>
     <y>    0.0 </y>
     <z>  -16.0 </z>
   </location>
   <direction>
     <x>  -0.9995 </x>
     <y>   0.0    </y>
     <z>   0.01 </z>
   </direction>
  </force>

 </external_reactions>


</fdm_config>