[Jsbsim-cvslogs] CVS: JSBSim/aircraft/Pterosaur Pterosaur.xml, NONE, 1.1

[Erik H. <eh...@us...>]

Update of /cvsroot/jsbsim/JSBSim/aircraft/Pterosaur
In directory sfp-cvs-1.v30.ch3.sourceforge.com:/tmp/cvs-serv27406/aircraft/Pterosaur

Added Files:
	Pterosaur.xml 
Log Message:
Add a engineless model of a Pterosaur that uses whing motion to geenrate lift and thrust

--- NEW FILE ---
<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>

<fdm_config name="Pterosaur" 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 2.9.9 </author>
  <filecreationdate> 27 Oct 2015 </filecreationdate>
  <version>$Revision: 1.1 $</version>
  <description> Models a Pterosaur. </description>
 </fileheader>

<!--
  File:     Pterosaur.xml
  Inputs:
    name:          Pterosaur
    type:          glider
    max weight:   352.02 lb
    wing span:     36.75 ft
    length:        32.81 ft
    wing area:     47.36 sq-ft

    gear type:     taildragger
    steering type: steering
    retractable?:  yes

  Outputs:
    wing loading:  9.54 lb/sq-ft
    payload:       104.87 lbs
    CL-alpha:      5.50 per radian
    CL-0:          0.25
    CL-max:        1.40
    CD-0:          0.01
    K:             0.02

  References:
   * "Flight in slow motion: aerodynamics of the pterosaur wing"
      http://rspb.royalsocietypublishing.org/content/278/1713/1881.full.pdf

   * "Student guest blog post: pterosaur weight estimation"
      http://lorenabarba.com/blog/student-guest-blog-post-pterosaur-weight-estimation/

   *  "Pterosaur flight"
      http://www.transitionrig.com/pterosau.htm

      "These animals were capable of active, flapping flight, accelerating from
      launch to cruise in approximately 15-20 wing strokes. The two animals
      both had a very high aspect ratio and did not connect the flight membrane
      (patagium) to the leg (which carried its own uropatagium and together
      with the tiny biological tail, formed an aerodynamic tail structure).
      When soaring, they both had an L/D max on the rough order of 28:1 (about
      equal to the Carbon Dragon and the WinDancer, and in the case of Qn a
      a similar gross weight), and actively modified their wing planform in a
      manner somewhat similar to birds, but controlled sail camber, chord, and
      planform in the outer wing membrane with fine structures called
      aktinofibrils which were generally oriented more diagonally than sail
      battens. The aktinofibrils worked in diagonal tension, maintaining a
      camber somewhat similar to Selig's S1223, but with a thinner airfoil
      section (outboard, that is - inboard at the elbow (which for Qn measured
      10.5 inches from top to bottom, T/C max was about 32% and the
      aktinofibril orientation was more amorphous).

      Throughout the wing, zero lift occurred at about -8 to -10.5 degrees,
      with a quarter chord pitching moment about -0.3."

   * "The principle of flight of ornithopters"
      http://www.ornithopter.de/english/principle.htm
-->

 <metrics>
   <wingarea  unit="FT2">    47.36 </wingarea>
   <wingspan  unit="FT" >    36.75 </wingspan>
   <wing_incidence>           2.00 </wing_incidence>
   <chord     unit="FT" >     1.29 </chord>
   <htailarea unit="FT2">    63.70 </htailarea>
   <htailarm  unit="FT" >    16.46 </htailarm>
   <vtailarea  unit="FT2">    4.74 </vtailarea>
   <vtailarm  unit="FT" >    16.41 </vtailarm>
   <location name="AERORP" unit="IN">
     <x>   188.99 </x>
     <y>     0.00 </y>
     <z>     0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>    51.18 </x>
     <y>   -18.00 </y>
     <z>    45.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>     0.0 </x>
     <y>     0.0 </y>
     <z>     0.0 </z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">    166.83 </ixx>
   <iyy unit="SLUG*FT2">    242.14 </iyy>
   <izz unit="SLUG*FT2">    361.58 </izz>
   <emptywt unit="LBS" >    187.26 </emptywt>
   <location name="CG" unit="IN">
     <x>   188.99 </x>
     <y>     0.00 </y>
     <z>    -9.84 </z>
   </location>
 </mass_balance>

 <propulsion>

   <engine file="dummy">
    <location unit="IN">
      <x>    36.00 </x>
      <y>     0.00 </y>
      <z>     0.00 </z>
    </location>
    <orient unit="DEG">
      <pitch>     0.00 </pitch>
       <roll>     0.00 </roll>
        <yaw>     0.00 </yaw>
    </orient>
    <feed> 0 </feed>

    <thruster file="direct">
     <sense> 1 </sense>
     <location unit="IN">
       <x>    36.00 </x>
       <y>     0.00 </y>
       <z>     0.00 </z>
     </location>
     <orient unit="DEG">
       <pitch>     0.00 </pitch>
        <roll>     0.00 </roll>
         <yaw>     0.00 </yaw>
     </orient>
    </thruster>
  </engine>
 </propulsion>

 <ground_reactions>

  <contact type="BOGEY" name="TAIL">
    <location unit="IN">
      <x>   253.18 </x>
      <y>     0.00 </y>
      <z>   -65.62 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.05 </dynamic_friction>
    <rolling_friction> 0.001 </rolling_friction>
    <spring_coeff  unit="LBS/FT">     352 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 176 </damping_coeff>
    <max_steer unit="DEG"> 0.50 </max_steer>
    <brake_group> NONE </brake_group>
    <retractable> 1 </retractable>
  </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
    <location unit="IN">
      <x>   171.98 </x>
      <y>   -39.69 </y>
      <z>   -78.74 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.05 </dynamic_friction>
    <rolling_friction> 0.001 </rolling_friction>
    <spring_coeff  unit="LBS/FT">     352 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 176 </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>   171.98 </x>
      <y>    39.69 </y>
      <z>   -78.74 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.05 </dynamic_friction>
    <rolling_friction> 0.001 </rolling_friction>
    <spring_coeff  unit="LBS/FT">     352 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 176 </damping_coeff>
    <max_steer unit="DEG">0</max_steer>
    <brake_group> RIGHT </brake_group>
    <retractable> 1 </retractable>
  </contact>

<!--
  <contact type="STRUCTURE" name="BELLY">
    <location unit="IN">
     <x>     0.00 </x>
     <y>     0.00 </y>
     <z>    -9.84 </z>
    </location>
   <static_friction>  0.3 </static_friction>
   <dynamic_friction> 0.2 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      5500 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 550 </damping_coeff>
  </contact>
-->

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x>   188.99 </x>
     <y>   -18.38 </y>
     <z>    -9.84 </z>
    </location>
   <static_friction>  1 </static_friction>
   <dynamic_friction> 1 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      352 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 352 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x>   188.99 </x>
     <y>    18.38 </y>
     <z>    -9.84 </z>
    </location>
   <static_friction>  1 </static_friction>
   <dynamic_friction> 1 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      352 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 352 </damping_coeff>
  </contact>

 </ground_reactions>

 <system file="Ornithopter Controls.xml"/>
 <system file="Landing Gear.xml"/>
 <system file="Wing Motion.xml"/>

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

 <aerodynamics>

  <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        1.3910
           0.1000        1.2350
           0.1500        1.1670
           0.2000        1.1350
           0.3000        1.0850
           0.4000        1.1020
           0.5000        1.0350
           0.6000        1.0240
           0.7000        1.0150
           0.8000        1.0110
           0.9000        1.0060
           1.0000        1.0040
           1.1000        1.0000
        </tableData>
      </table>
    </product>
  </function>

  <axis name="LIFT">

    <function name="aero/force/Lift_alpha">
      <description>Lift due to alpha of the body</description>
      <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
             -12.0   -0.750
              0.00    0.250
              12.0    1.400
              35.0    0.710
            </tableData>
          </table>
      </product>
    </function>

    <function name="aero/force/Lift_wing_incidence">
      <description>Lift due to alpha of the wings</description>
      <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">fcs/wing-alpha-deg</independentVar>
            <tableData>
             -15.0    0.0
             -10.0    0.4
              -5.0    1.0
               0.0    1.5
               5.0    2.0
              10.0    1.9
              15.0    1.5
              20.0    1.0
            </tableData>
          </table>
      </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> 0.0800 </value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">

    <function name="aero/force/Drag_wing_incidence">
       <description>Delta Drag due to wing angle</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">fcs/wing-alpha-deg</independentVar>
            <tableData>
             -30.0   -0.800
             -25.0   -0.450
             -20.0   -0.275
             -15.0   -0.080
             -10.0   -0.050
              -5.0   -0.030
               0.0    0.000
               5.0    0.000
              10.0    0.001
              15.0    0.009
              20.0    0.011
              25.0    0.013
              30.0    0.020
            </tableData>
          </table>
       </product>
    </function>

    <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-deg</independentVar>
            <tableData>
             -90.0    1.5000
             -60.0    0.0110
               0.0    0.0090
              60.0    0.0110
              90.0    1.5000
            </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> 0.0095 </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-deg</independentVar>
            <tableData>
              -90.0    1.2300
              -15.0    0.0500
               0.00    0.0000
               15.0    0.0500
               90.0    1.2300
            </tableData>
          </table>
       </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> 0.1110 </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> -1.0000 </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> -0.2500 </value>
       </product>
    </function>

    <function name="aero/moment/Pitch_wing_incidence">
      <description>Pitch due to alpha of the wings</description>
      <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <table>
            <independentVar lookup="row">fcs/wing-alpha-deg</independentVar>
            <tableData>
              -5.0    0.0
               0.0   -0.0251
               5.0   -0.0628
              10.0   -0.0942
              15.0   -0.1256
              20.0   -0.1193
              25.0   -0.0942
              30.0   -0.0628
            </tableData>
          </table>
      </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>
          <value> -0.8000 </value>
       </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> -12.0000 </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> -9.0000 </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> -0.1000 </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> -0.4000 </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> 0.1500 </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> 0.0700 </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> 0.1200 </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> -0.1500 </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> -0.0100 </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>-0.019</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

 <external_reactions>
 </external_reactions>

</fdm_config>