jsbsim.js
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JSBSim flight dynamics model ported to JavaScript
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text/xml
<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>
<author> David Culp </author>
<filecreationdate> 2007-01-16 </filecreationdate>
<version> 0.0 </version>
<description> Models a F4N. </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: 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" > 38.40 </wingspan>
<wing_incidence> 2.00 </wing_incidence>
<chord unit="FT" > 13.80 </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>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x> -261.59 </x>
<y> 0.00 </y>
<z> -62.72 </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"> 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> -71.47 </y>
<z> -63.72 </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> 71.47 </y>
<z> -63.72 </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>
</ground_reactions>
<external_reactions>
<force name="catapult" frame="LOCAL">
<location unit="IN">
<x> -260.0 </x>
<y> 0.0 </y>
<z> 0.0 </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="LOCAL">
<location unit="IN">
<x> 230.0 </x>
<y> 0.0 </y>
<z> -30.0 </z>
</location>
<direction>
<x> 0.9902681 </x>
<y> 0.1391731 </y>
<z> 0.01 </z>
</direction>
</force>
</external_reactions>
<propulsion>
<engine file="J79-GE-11A">
<location unit="IN">
<x> 190 </x>
<y> -20.00 </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">
<location unit="IN">
<x> 190 </x>
<y> -20.00 </y>
<z> -18.9 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </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>
<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> 190 </x>
<y> 20.00 </y>
<z> -18.9 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </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> 0.00 </y>
<z> -18.90 </z>
</location>
<capacity unit="LBS"> 13160.00 </capacity>
<contents unit="LBS"> 13000.00 </contents>
</tank>
</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"/>
<!--
<flight_control name="FCS">
</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 -0.64
0.00 0.08
0.26 1.00
0.40 0.95
0.60 0.40
1.30 0.05
</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> 0.4 </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>
</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 0.031
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/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>
<property>fcs/elevator-pos-norm</property>
<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>
</fdm_config>