jsbsim.js
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JSBSim flight dynamics model ported to JavaScript
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text/xml
<fdm_config name="Pogo" 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 0.91 </author>
<filecreationdate> 2009-07-24 </filecreationdate>
<version>$Revision: 1.2 $</version>
<description> Models a Pogo. </description>
<note>
This model was created using publicly available data, publicly available
technical reports, textbooks, and guesses. It contains no proprietary or
restricted data. If this model has been validated at all, it would be
only to the extent that it seems to "fly right", and that it possibly
complies with published, publicly known, performance data (maximum speed,
endurance, etc.). Thus, this model is meant for educational and entertainment
purposes only.
This simulation model is not endorsed by the manufacturer. This model is not
to be sold.
</note>
</fileheader>
<!--
File: Pogo.xml
Inputs:
name: Pogo
type: WWII fighter, subsonic sport, aerobatic
max weight: 16000.0 lb
wing span: 25.3 ft
length: 29.1 ft
wing area: 336.5 sq-ft
gear type: taildragger
retractable?: yes
# engines: 1
engine type: piston
engine layout: forward fuselage
yaw damper? no
Outputs:
wing loading: 47.55 lb/sq-ft
CL-alpha: 4.5 per radian
CL-0: 0.17
CL-max: 1.2
CD-0: 0.02
K: 0.06
-->
<metrics>
<wingarea unit="FT2"> 336.50 </wingarea>
<wingspan unit="FT" > 25.30 </wingspan>
<wing_incidence> 2.00 </wing_incidence>
<chord unit="FT" > 13.30 </chord>
<htailarea unit="FT2"> 57.21 </htailarea>
<htailarm unit="FT" > 17.46 </htailarm>
<vtailarea unit="FT2"> 33.65 </vtailarea>
<vtailarm unit="FT" > 17.46 </vtailarm>
<location name="AERORP" unit="IN">
<x> 139.68 </x>
<y> 0.00 </y>
<z> 0.00 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 97.78 </x>
<y> 0.00 </y>
<z> 40.00 </z>
</location>
<location name="VRP" unit="IN">
<x>0</x>
<y>0</y>
<z>0</z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 12016 </ixx>
<iyy unit="SLUG*FT2"> 23361 </iyy>
<izz unit="SLUG*FT2"> 30647 </izz>
<emptywt unit="LBS" > 11700 </emptywt>
<location name="CG" unit="IN">
<x> 139.68 </x>
<y> 0.00 </y>
<z> -8.73 </z>
</location>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="LEFT">
<location unit="IN">
<x> 200 </x>
<y>-154 </y>
<z> 0 </z>
</location>
<orientation unit="DEG">
<pitch>-80.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orientation>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 8000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600.00 </damping_coeff>
<max_steer unit="DEG">360</max_steer>
<brake_group>LEFT</brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="RIGHT">
<location unit="IN">
<x> 200 </x>
<y> 154 </y>
<z> 0 </z>
</location>
<orientation unit="DEG">
<pitch>-80.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orientation>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 8000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600.00 </damping_coeff>
<max_steer unit="DEG">360</max_steer>
<brake_group>RIGHT</brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="TAIL">
<location unit="IN">
<x> 200 </x>
<y> 0.00 </y>
<z> 128 </z>
</location>
<orientation unit="DEG">
<pitch>-80.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orientation>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 8000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600.00 </damping_coeff>
<max_steer unit="DEG"> 360 </max_steer>
<brake_group>NONE</brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="Fin">
<location unit="IN">
<x> 200 </x>
<y> 0.00 </y>
<z> -128 </z>
</location>
<orientation unit="DEG">
<pitch>-80.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orientation>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 8000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600.00 </damping_coeff>
<max_steer unit="DEG"> 360 </max_steer>
<brake_group>NONE</brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="NOSE">
<location unit="IN">
<x>-160 </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"> 3200.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 640.00 </damping_coeff>
</contact>
<!--
<contact type="STRUCTURE" name="LEFT_WING">
<location unit="IN">
<x> 139.68 </x>
<y> -12.65 </y>
<z> -8.73 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 16000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 3200.00 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="IN">
<x> 139.68 </x>
<y> 12.65 </y>
<z> -8.73 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 16000.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 3200.00 </damping_coeff>
</contact>
-->
</ground_reactions>
<propulsion>
<engine file="YT40-A-16">
<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>
<feed>1</feed>
<thruster file="Pogo_prop">
<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>
<sense> 1.0 </sense>
<p_factor> 1.0 </p_factor>
</thruster>
</engine>
<tank type="FUEL" number="0">
<location unit="IN">
<x> 139.68 </x>
<y> 0.00 </y>
<z> -8.73 </z>
</location>
<capacity unit="LBS"> 1000.00 </capacity>
<contents unit="LBS"> 500.00 </contents>
</tank>
<tank type="FUEL" number="1">
<location unit="IN">
<x> 139.68 </x>
<y> 0.00 </y>
<z> -8.73 </z>
</location>
<capacity unit="LBS"> 1000.00 </capacity>
<contents unit="LBS"> 500.00 </contents>
</tank>
</propulsion>
<flight_control name="FCS: Pogo">
<channel name="Pitch">
<summer name="Pitch Trim Sum">
<input>fcs/elevator-cmd-norm</input>
<input>fcs/pitch-trim-cmd-norm</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>
<aerosurface_scale name="Elevator Control">
<input>fcs/pitch-trim-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="elevator normalization">
<input>fcs/elevator-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="Roll Trim Sum">
<input>fcs/aileron-cmd-norm</input>
<input>fcs/roll-trim-cmd-norm</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>
<aerosurface_scale name="Left Aileron Control">
<input>fcs/roll-trim-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Control">
<input>fcs/roll-trim-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="left aileron normalization">
<input>fcs/left-aileron-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="right aileron normalization">
<input>fcs/right-aileron-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/right-aileron-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Yaw">
<summer name="Rudder Command Sum">
<input>fcs/rudder-cmd-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min> -0.35 </min>
<max> 0.35 </max>
</clipto>
</summer>
<aerosurface_scale name="Rudder Control">
<input>fcs/rudder-command-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="rudder normalization">
<input>fcs/rudder-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/rudder-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Flaps">
<kinematic name="Flaps Control">
<input>fcs/flap-cmd-norm</input>
<traverse>
<setting>
<position> 0 </position>
<time> 0 </time>
</setting>
<setting>
<position> 15 </position>
<time> 4 </time>
</setting>
<setting>
<position> 30 </position>
<time> 3 </time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="flap normalization">
<input>fcs/flap-pos-deg</input>
<domain>
<min> 0 </min>
<max> 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/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-0.20 -0.730
0.00 0.170
0.23 1.200
0.60 0.582
</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-deg</property>
<value> 0.01000 </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</value>
</product>
</function>
<function name="aero/coefficient/CLde">
<description>Lift_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<value>0.2</value>
</product>
</function>
</axis>
<axis name="DRAG">
<function name="aero/coefficient/CD0">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-1.57 1.500
-0.26 0.026
0.00 0.020
0.26 0.026
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>0.06</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
0.75 0.000
1.10 0.023
1.80 0.015
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDflap">
<description>Drag_due_to_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-deg</property>
<value> 0.00133 </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>0.03</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>0.02</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>0.04</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/Clprop">
<description>HACK_Roll_moment_countering_prop_torque</description>
<product>
<property>moments/l-prop-lbsft</property>
<value>-1.0</value>
</product>
</function>
<function name="aero/coefficient/Clb">
<description>Roll_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<value>-0.1</value>
</product>
</function>
<function name="aero/coefficient/Clp">
<description>Roll_moment_due_to_roll_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<value>-0.4</value>
</product>
</function>
<function name="aero/coefficient/Clr">
<description>Roll_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>0.15</value>
</product>
</function>
<function name="aero/coefficient/Clda">
<description>Roll_moment_due_to_aileron</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.0 0.180
2.0 0.060
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cldr">
<description>Roll_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>0.01</value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/coefficient/Cmalpha">
<description>Pitch_moment_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-3.14159 0.0
-2.36 -0.175
-1.57 0.0
-0.7 0.175
-0.35 0.175
0.0 0.0
0.35 -0.175
0.7 -0.175
1.57 0.0
2.36 0.175
3.14159 0.0
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmde">
<description>Pitch_moment_due_to_elevator</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elevator-pos-rad</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.0 -1.000
2.0 -0.250
</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>-15</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>-7</value>
</product>
</function>
</axis>
<axis name="YAW">
<function name="aero/coefficient/Cnb">
<description>Yaw_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<value>0.12</value>
</product>
</function>
<function name="aero/coefficient/Cnr">
<description>Yaw_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>-0.15</value>
</product>
</function>
<function name="aero/coefficient/Cndr">
<description>Yaw_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>-0.1</value>
</product>
</function>
<function name="aero/coefficient/Cnda">
<description>Adverse_yaw</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<value>-0.003</value>
</product>
</function>
</axis>
</aerodynamics>
<output name="pogo.csv" type="CSV" rate="20">
<simulation> OFF </simulation>
<atmosphere> OFF </atmosphere>
<massprops> OFF</massprops>
<aerosurfaces> OFF </aerosurfaces>
<rates> OFF </rates>
<forces> OFF </forces>
<moments> ON </moments>
<position> ON </position>
<propulsion> ON </propulsion>
<velocities> OFF </velocities>
<fcs> OFF </fcs>
<ground_reactions> ON </ground_reactions>
<coefficients> OFF </coefficients>
<!--property> moments/l-prop-lbsft </property-->
</output>
</fdm_config>