A310-204.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="A310-204" 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 0.95 </author>
    <filecreationdate>2014-01-20</filecreationdate>
    <version>$Revision: 1.15 $</version>
    <description> Models a A310-204. </description>
  </fileheader>

  <!--
  File:     A310-204.xml
  Inputs:
  name:          A310-204
  type:          two-engine transonic transport
  max weight:    330750 lb
  wing span:     144.00309 ft
  length:        148.07153 ft
  wing area:     2357.526459 sq-ft
  gear type:     tricycle
  retractable?:  yes
  # engines:     2
  engine type:   turbine
  engine layout: wings
  yaw damper?    yes
  Outputs:
  wing loading:  140.30 lb/sq-ft
  payload:       40682.2 lbs
  CL-alpha:      4.4 per radian
  CL-0:          0.2
  CL-max:        1.2
  CD-0:          0.02
  K:             0.043

  -->

  <metrics>
    <wingarea  unit="FT2"> 2357.53 </wingarea>
    <wingspan  unit="FT" >  144.00 </wingspan>
    <wing_incidence>          2.00 </wing_incidence>
    <chord     unit="FT" >   16.37 </chord>
    <htailarea unit="FT2">  688.96 </htailarea>
    <htailarm  unit="FT" >   73.82 </htailarm>
    <vtailarea unit="FT2">  486.58 </vtailarea>
    <vtailarm  unit="FT" >   66.28 </vtailarm>
    <location name="AERORP" unit="IN">
      <x> 890.99 </x>
      <y>   0.00 </y>
      <z>   0.00 </z>
    </location>
    <location name="EYEPOINT" unit="IN">
      <x> 124.38 </x>
      <y> -30.00 </y>
      <z>  70.00 </z>
    </location>
    <location name="VRP" unit="IN">
      <x>0</x>
      <y>0</y>
      <z>0</z>
    </location>
  </metrics>

  <mass_balance>
    <ixx unit="SLUG*FT2">   1996912 </ixx>
    <iyy unit="SLUG*FT2">   4878042 </iyy>
    <izz unit="SLUG*FT2">   6953101 </izz>
    <emptywt unit="LBS" >    198450 </emptywt>
    <location name="CG" unit="IN">
      <x> 890.99 </x>
      <y>   0.00 </y>
      <z> -44.42 </z>
    </location>
    <pointmass name="Payload">
      <description> 40682 LBS + full (91618 LBS) fuel should bring model up to entered max weight</description>
      <weight unit="LBS">  20341.1 </weight>
      <location name="POINTMASS" unit="IN">
	<x> 890.99 </x>
	<y>   0.00 </y>
	<z> -44.42 </z>
      </location>
    </pointmass> 
  </mass_balance>

  <ground_reactions>

    <contact type="BOGEY" name="NOSE">
      <location unit="IN">
	<x> 230.99 </x>
	<y>   0.00 </y>
	<z> -213.22 </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">      99225.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 165375.00 </damping_coeff>
      <max_steer unit="DEG"> 35.00 </max_steer>
      <brake_group>NONE</brake_group>
      <retractable>1</retractable>
    </contact>

    <contact type="BOGEY" name="LEFT_MAIN">
      <location unit="IN">
	<x> 926.63 </x>
	<y> -155.52 </y>
	<z> -213.22 </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">      330750.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 165375.00 </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> 926.63 </x>
	<y> 155.52 </y>
	<z> -213.22 </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">      330750.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 165375.00 </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> 890.99 </x>
	<y> -72.00 </y>
	<z> -44.42 </z>
      </location>
      <static_friction>  1.00 </static_friction>
      <dynamic_friction> 1.00 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      330750.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 330750.00 </damping_coeff>
    </contact>

    <contact type="STRUCTURE" name="RIGHT_WING">
      <location unit="IN">
	<x> 890.99 </x>
	<y>  72.00 </y>
	<z> -44.42 </z>
      </location>
      <static_friction>  1.00 </static_friction>
      <dynamic_friction> 1.00 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      330750.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 330750.00 </damping_coeff>
    </contact>

  </ground_reactions>

  <propulsion>

    <engine file="GE-CF6-80C2A2">
      <location unit="IN">
	<x> 890.99 </x>
	<y> -288.01 </y>
	<z> -40.00 </z>
      </location>
      <orient unit="DEG">
	<pitch> 0.00 </pitch>
	<roll>  0.00 </roll>
	<yaw>   0.00 </yaw>
      </orient>
      <feed>0</feed>
      <thruster file="direct">
	<location unit="IN">
	  <x> 890.99 </x>
	  <y> -288.01 </y>
	  <z> -40.00 </z>
	</location>
	<orient unit="DEG">
	  <pitch> 0.00 </pitch>
	  <roll>  0.00 </roll>
	  <yaw>   0.00 </yaw>
	</orient>
      </thruster>
    </engine>

    <engine file="GE-CF6-80C2A2">
      <location unit="IN">
	<x> 890.99 </x>
	<y> 288.01 </y>
	<z> -40.00 </z>
      </location>
      <orient unit="DEG">
	<pitch> 0.00 </pitch>
	<roll>  0.00 </roll>
	<yaw>   0.00 </yaw>
      </orient>
      <feed>1</feed>
      <thruster file="direct">
	<location unit="IN">
	  <x> 890.99 </x>
	  <y> 288.01 </y>
	  <z> -40.00 </z>
	</location>
	<orient unit="DEG">
	  <pitch> 0.00 </pitch>
	  <roll>  0.00 </roll>
	  <yaw>   0.00 </yaw>
	</orient>
      </thruster>
    </engine>

    <tank type="FUEL" number="0">
      <location unit="IN">
	<x> 890.99 </x>
	<y>   0.00 </y>
	<z> -44.42 </z>
      </location>
      <capacity unit="LBS"> 30539.25 </capacity>
      <contents unit="LBS"> 15269.63 </contents>
    </tank>

    <tank type="FUEL" number="1">
      <location unit="IN">
	<x> 890.99 </x>
	<y>   0.00 </y>
	<z> -44.42 </z>
      </location>
      <capacity unit="LBS"> 30539.25 </capacity>
      <contents unit="LBS"> 15269.63 </contents>
    </tank>

    <tank type="FUEL" number="2">
      <location unit="IN">
	<x> 890.99 </x>
	<y>   0.00 </y>
	<z> -44.42 </z>
      </location>
      <capacity unit="LBS"> 30539.25 </capacity>
      <contents unit="LBS"> 15269.63 </contents>
    </tank>

  </propulsion>

  <flight_control name="FCS: A310-308">

    <channel name="Pitch">

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

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

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

    </channel>

    <channel name="Roll">

      <summer name="Roll Trim Sum">
	<input>fcs/aileron-cmd-norm</input>
	<input>fcs/roll-trim-cmd-norm</input>
	<clipto>
          <min> -1 </min>
          <max>  1 </max>
	</clipto>
      </summer>

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

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

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

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

    </channel>

    <property value="1">fcs/yaw-damper-enable</property>
    <channel name="Yaw">

      <summer name="Rudder Command Sum">
	<input>fcs/rudder-cmd-norm</input>
	<input>fcs/yaw-trim-cmd-norm</input>
	<clipto>
          <min> -1 </min>
          <max>  1 </max>
	</clipto>
      </summer>

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

      <summer name="Rudder Sum">
	<input>fcs/rudder-command-sum</input>
	<input>fcs/yaw-damper-rate</input>
	<clipto>
          <min> -1.1 </min>
          <max>  1.1 </max>
	</clipto>
      </summer>

      <aerosurface_scale name="Rudder Control">
	<input>fcs/rudder-sum</input>
	<domain>
          <min> -1.1 </min>
          <max>  1.1 </max>
	</domain>
	<range>
          <min> -0.35 </min>
          <max>  0.35 </max>
	</range>
	<output>fcs/rudder-pos-rad</output>
      </aerosurface_scale>

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

    </channel>

    <channel name="Flaps">
      <kinematic name="Flaps Control">
	<input>fcs/flap-cmd-norm</input>
	<traverse>
	  <setting>
            <position>  0 </position>
            <time>      0 </time>
	  </setting>
	  <setting>
            <position>  10 </position>
            <time>      2 </time>
	  </setting>
	  <setting>
            <position>  15 </position>
            <time>      3 </time>
	  </setting>
	  <setting>
            <position> 20 </position>
            <time>      4 </time>
	  </setting>
	  <setting>
            <position> 40 </position>
            <time>      5 </time>
	  </setting>
	</traverse>
	<output>fcs/flap-pos-deg</output>
      </kinematic>

      <aerosurface_scale name="flap normalization">
	<input>fcs/flap-pos-deg</input>
	<domain>
          <min>  0 </min>
          <max> 30 </max>
	</domain>
	<range>
          <min> 0 </min>
          <max> 1 </max>
	</range>
	<output>fcs/flap-pos-norm</output>
      </aerosurface_scale>

    </channel>

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

    </channel>

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

    </channel>

  </flight_control>

  <aerodynamics>

    <axis name="LIFT">

      <function name="aero/force/Lift_alpha">
	<description>Lift due to alpha</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -0.20 -0.680
              0.00  0.200
              0.23  1.200
              0.60  0.600
            </tableData>
          </table>
	</product>
      </function>

      <function name="aero/force/Lift_flap">
	<description>Delta Lift due to flaps</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/flap-pos-deg</property>
          <value> 0.03500 </value>
	</product>
      </function>

      <function name="aero/force/Lift_speedbrake">
	<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>-0.1</value>
	</product>
      </function>

      <function name="aero/force/Lift_elevator">
	<description>Lift due to Elevator Deflection</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/elevator-pos-rad</property>
          <value>0.2</value>
	</product>
      </function>

    </axis>

    <axis name="DRAG">

      <function name="aero/force/Drag_basic">
	<description>Drag at zero lift</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -1.57    1.500
              -0.26    0.026
              0.00    0.020
              0.26    0.026
              1.57    1.500
            </tableData>
          </table>
	</product>
      </function>

      <function name="aero/force/Drag_induced">
	<description>Induced drag</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/cl-squared</property>
          <value>0.043</value>
        </product>
      </function>

      <function name="aero/force/Drag_mach">
	<description>Drag due to mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.00      0.000
              0.79      0.000
              1.10      0.023
              1.80      0.015
            </tableData>
          </table>
        </product>
      </function>

      <function name="aero/force/Drag_flap">
	<description>Drag due to flaps</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/flap-pos-deg</property>
          <value> 0.00197 </value>
        </product>
      </function>

      <function name="aero/force/Drag_gear">
	<description>Drag due to gear</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>gear/gear-pos-norm</property>
          <value>0.015</value>
        </product>
      </function>

      <function name="aero/force/Drag_speedbrake">
	<description>Drag due to speedbrakes</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/speedbrake-pos-norm</property>
          <value>0.02</value>
        </product>
      </function>

      <function name="aero/force/Drag_beta">
	<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/force/Drag_elevator">
	<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>0.04</value>
	</product>
      </function>

    </axis>

    <axis name="SIDE">

      <function name="aero/force/Side_beta">
	<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/moment/Roll_beta">
	<description>Roll moment due to beta</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/beta-rad</property>
          <value>-0.1</value>
	</product>
      </function>

      <function name="aero/moment/Roll_damp">
	<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/moment/Roll_yaw">
	<description>Roll moment due to yaw rate</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/bi2vel</property>
          <property>velocities/r-aero-rad_sec</property>
          <value>0.15</value>
	</product>
      </function>

      <function name="aero/moment/Roll_aileron">
	<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>
          <value>0.1</value>
	</product>
      </function>

      <function name="aero/moment/Roll_rudder">
	<description>Roll moment due to rudder</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/rudder-pos-rad</property>
          <value>0.01</value>
	</product>
      </function>

    </axis>

    <axis name="PITCH">

      <function name="aero/moment/Pitch_alpha">
	<description>Pitch moment due to alpha</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>aero/alpha-rad</property>
          <value>-0.6</value>
	</product>
      </function>

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

      <function name="aero/moment/Pitch_damp">
	<description>Pitch moment due to pitch rate</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>aero/ci2vel</property>
          <property>velocities/q-aero-rad_sec</property>
          <value>-17</value>
	</product>
      </function>

      <function name="aero/moment/Pitch_alphadot">
	<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/moment/Yaw_beta">
	<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/moment/Yaw_damp">
	<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/moment/Yaw_rudder">
	<description>Yaw moment due to rudder</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/rudder-pos-rad</property>
          <value>-0.1</value>
	</product>
      </function>

      <function name="aero/moment/Yaw_aileron">
	<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>
  </external_reactions>

</fdm_config>