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A350-family/A350-900-jsbsim.xml

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Initial commit Signed-off-by: fly <merspieler@airmail.cc>
2020-07-18 14:49:38 +00:00
<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" name="A350XWB-900-jsbsim" version="2.0" release="BETA" xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Bicyus (Jon Ortuondo) </author>
<email> bicyus@gmail.com </email>
<filecreationdate> 2012-03-09 </filecreationdate>
<version> 0.01 </version>
<description>Airbus A350XWB - 900</description>
<note/>
<limitation/>
</fileheader>
<metrics>
<!-- lenght 66.61 m -->
<wingarea unit="M2">460</wingarea>
<wingspan unit="M">64.8</wingspan>
<wing_incidence>2</wing_incidence> <!--Guestimate (Model inaccurate)-->
<chord unit="M">7.38</chord>
<htailarea unit="M2">70.92</htailarea>
<htailarm unit="M">19.29</htailarm>
<vtailarea unit="M2">49.64</vtailarea>
<vtailarm unit="M">9.42</vtailarm>
<!--
<location name="AERORP" unit="IN">
<x> 642.122 </x>
<y> 0 </y>
<z> -25.2091 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 80 </x>
<y> -30 </y>
<z> 70 </z>
</location>
-->
<location name="VRP" unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
</metrics>
<mass_balance>
<!--ixx unit="SLUG*FT2"> 611903 </ixx>
<iyy unit="SLUG*FT2"> 1735389 </iyy>
<izz unit="SLUG*FT2"> 2301293 </izz-->
<!--
___________________A320_________A330__________A340
BOW_____________178000________270000________283925
SPAN______________144___________198___________209
LENGTH____________153___________209___________209
ROLL MOI_________1725000______5727777_______10613448
PITCH MOI________2550000______19040141_______13904249
YAW MOI_________3950000______23089847_______24848934
<ixx unit="SLUG*FT2"> 2262183 </ixx>
<iyy unit="SLUG*FT2"> 3172439 </iyy>
<izz unit="SLUG*FT2"> 3337024 </izz>
-->
<ixx unit="SLUG*FT2">1725000</ixx>
<iyy unit="SLUG*FT2">2550000</iyy>
<izz unit="SLUG*FT2">3950000</izz>
<ixy unit="SLUG*FT2"> 0 </ixy>
<ixz unit="SLUG*FT2"> 0 </ixz>
<iyz unit="SLUG*FT2"> 0 </iyz>
<emptywt unit="LBS">229100</emptywt>
<location name="CG" unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<pointmass name="Crew">
<weight unit="LBS">400</weight>
<location name="POINTMASS" unit="IN">
<x>-1165.35</x>
<y>0</y>
<z>0</z>
</location>
</pointmass>
<pointmass name="PAX">
<weight unit="LBS">40000</weight>
<form shape="cylinder">
<radius unit="M"> 5.6 </radius>
<length unit="M"> 40 </length>
</form>
<location name="POINTMASS" unit="IN">
<x>-300</x>
<y>0</y>
<z>0</z>
</location>
</pointmass>
<pointmass name="Fwd Cargo">
<weight unit="LBS">7000</weight>
<form shape="cylinder">
<radius unit="M"> 3 </radius>
<length unit="M"> 18 </length>
</form>
<location name="POINTMASS" unit="IN">
<x>-800</x>
<y>0</y>
<z>0</z>
</location>
</pointmass>
<pointmass name="Aft Cargo">
<weight unit="LBS">0</weight>
<form shape="cylinder">
<radius unit="M"> 2 </radius>
<length unit="M"> 5 </length>
</form>
<location name="POINTMASS" unit="IN">
<x>638</x>
<y>0</y>
<z>0</z>
</location>
</pointmass>
<pointmass name="Rear Bulk Cargo">
<weight unit="LBS">0</weight>
<form shape="cylinder">
<radius unit="M"> 1.24 </radius>
<length unit="M"> 2 </length>
</form>
<location name="POINTMASS" unit="IN">
<x>874</x>
<y>0</y>
<z>0</z>
</location>
</pointmass>
<pointmass name="Engine1">
<weight unit="LBS">13000</weight>
<form shape="cylinder">
<radius unit="M"> 1.31 </radius>
<length unit="M"> 5 </length>
</form>
<location name="POINTMASS" unit="IN">
<x>-307</x>
<y>-404</y>
<z>54</z>
</location>
</pointmass>
<pointmass name="Engine2">
<weight unit="LBS">13000</weight>
<form shape="cylinder">
<radius unit="M"> 1.31 </radius>
<length unit="M"> 5 </length>
</form>
<location name="POINTMASS" unit="IN">
<x>-307</x>
<y>404</y>
<z>54</z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE_LG">
<location unit="IN">
<x> -1109.03 </x>
<y> 0 </y>
<z> -157.33 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
<max_steer unit="DEG"> 70 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MLG">
<location unit="IN">
<x> -11.42 </x>
<y> -210.04 </y>
<z> -157.87 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 100000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MLG">
<location unit="IN">
<x> -11.42 </x>
<y> 210.04 </y>
<z> -157.87 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 100000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
<!--Nose tip (VRP)-->
<contact type="STRUCTURE" name="NOSE_1">
<location unit="IN">
<x> -1291.33 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Under the nose if front gear was down-->
<contact type="STRUCTURE" name="NOSE_2">
<location unit="IN">
<x> -1138.98 </x>
<y> 0 </y>
<z> -56.69 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Nose top-->
<contact type="STRUCTURE" name="NOSE_3">
<location unit="IN">
<x> -986.61 </x>
<y> 0 </y>
<z> 176.77 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Center Bottom (Belly fairing)-->
<contact type="STRUCTURE" name="CENTER_1">
<location unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> -81.10 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Center Top-->
<contact type="STRUCTURE" name="CENTER_2">
<location unit="IN">
<x> -79.53 </x>
<y> 0 </y>
<z> 179.92 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="ENG_1">
<location unit="IN">
<x>-320.08</x>
<y>409.84</y>
<z>-128.74</z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="ENG_2">
<location unit="IN">
<x>-320.08</x>
<y>-409.84</y>
<z>-128.74</z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Normal tail strike position I guess-->
<contact type="STRUCTURE" name="TAIL_1">
<location unit="IN">
<x> 740.55 </x>
<y> 0 </y>
<z> -31.21 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Top of VSTAB-->
<contact type="STRUCTURE" name="TAIL_2">
<location unit="IN">
<x> 1233.07 </x>
<y> 0 </y>
<z> 514.57 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Left HSTAB-->
<contact type="STRUCTURE" name="TAIL_3">
<location unit="IN">
<x> 1327.95 </x>
<y> -371.65 </y>
<z> 137.79 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Right HSTAB-->
<contact type="STRUCTURE" name="TAIL_4">
<location unit="IN">
<x> 1327.95 </x>
<y> 371.65 </y>
<z> 137.79 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Left Wing-->
<contact type="STRUCTURE" name="WING_TIP_1">
<location unit="IN">
<x> 394.09 </x>
<y> -1153.94 </y>
<z> 116.54 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Left Wing tip-->
<contact type="STRUCTURE" name="WING_TIP_2">
<location unit="IN">
<x> 534.25 </x>
<y> -1274.41 </y>
<z> 207.87 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Right wing-->
<contact type="STRUCTURE" name="WING_TIP_3">
<location unit="IN">
<x> 394.09 </x>
<y> 1153.94 </y>
<z> 116.54 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!--Left Wing tip-->
<contact type="STRUCTURE" name="WING_TIP_4">
<location unit="IN">
<x> 534.25 </x>
<y> 1274.41 </y>
<z> 207.87 </z>
</location>
<static_friction> 1.0 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.4 </rolling_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
</ground_reactions>
<propulsion>
<engine file="trent_xwb">
<location unit="IN">
<x>-307</x>
<y>-404</y>
<z>54</z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 2.2 </pitch>
<yaw> 1 </yaw>
</orient>
<feed>5</feed>
<thruster file="direct">
<location unit="IN">
<x>-307</x>
<y>-404</y>
<z>54</z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 2.2 </pitch>
<yaw> 1 </yaw>
</orient>
</thruster>
</engine>
<engine file="trent_xwb">
<location unit="IN">
<x>-307</x>
<y>404</y>
<z>54</z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 2.2 </pitch>
<yaw> -1 </yaw>
</orient>
<feed>6</feed>
<thruster file="direct">
<location unit="IN">
<x>-307</x>
<y>404</y>
<z>54</z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 2.2 </pitch>
<yaw> -1 </yaw>
</orient>
</thruster>
</engine>
<engine file="APU">
<location unit="IN">
<x> 100 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<thruster file="direct">
<location unit="IN">
<x> 100 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<tank type="FUEL">
<!-- Left Tank (Wing tip Ventilation Surge) -->
<location unit="IN">
<x> 534 </x>
<y> -1274 </y>
<z> 207 </z>
</location>
<capacity unit="LBS"> 300 </capacity>
<contents unit="LBS"> 0 </contents>
<priority>0</priority>
<type>JET-A1</type>
<temperature>50</temperature>
</tank>
<tank type="FUEL">
<!-- Left Tank (Inner) -->
<location unit="IN">
<x> -41 </x>
<y> -333 </y>
<z> 51 </z>
</location>
<capacity unit="LBS"> 52238 </capacity>
<contents unit="LBS"> 30000 </contents>
<standpipe unit="LBS">31</standpipe>
<!-- minimun fuel on pipes -->
<priority>3</priority>
<type>JET-A1</type>
<temperature>50</temperature>
</tank>
<tank type="FUEL">
<!-- Center Tank -->
<location unit="IN">
<x> -183.46 </x>
<y> 0 </y>
<z> -59.05 </z>
</location>
<capacity unit="LBS"> 145366 </capacity>
<contents unit="LBS"> 64000 </contents>
<standpipe unit="LBS">43</standpipe>
<!-- minimun fuel on pipes -->
<priority>1</priority>
<type>JET-A1</type>
<temperature>50</temperature>
</tank>
<tank type="FUEL">
<!-- Right Tank (Inner) -->
<location unit="IN">
<x> -41 </x>
<y> 333 </y>
<z> 51 </z>
</location>
<capacity unit="LBS"> 52238 </capacity>
<contents unit="LBS"> 30000 </contents>
<standpipe unit="LBS">31</standpipe>
<!-- minimun fuel on pipes -->
<priority>3</priority>
<type>JET-A1</type>
<temperature>50</temperature>
</tank>
<tank type="FUEL">
<!-- Right Tank (Wing tip Ventilation Surge) -->
<location unit="IN">
<x> 534 </x>
<y> 1274 </y>
<z> 207 </z>
</location>
<capacity unit="LBS"> 300 </capacity>
<contents unit="LBS"> 0 </contents>
<priority>0</priority>
<type>JET-A1</type>
<temperature>50</temperature>
</tank>
<tank type="FUEL">
<!-- LEFT FUEL PIPES (Engine 1 feed from this) -->
<location unit="IN">
<x> -320 </x>
<y> -409 </y>
<z> -128 </z>
</location>
<capacity unit="LBS"> 100 </capacity>
<contents unit="LBS"> 100 </contents>
<priority>1</priority>
<type>JET-A1</type>
</tank>
<tank type="FUEL">
<!-- RIGHT FUEL PIPES (Engine 2 feed from this) -->
<location unit="IN">
<x> -320 </x>
<y> 409 </y>
<z> -128 </z>
</location>
<capacity unit="LBS"> 100 </capacity>
<contents unit="LBS"> 100 </contents>
<priority>1</priority>
<type>JET-A1</type>
</tank>
</propulsion>
<system file="fuel"/>
<flight_control name="FCS: A350">
<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>
<gain>0.018</gain>
<range>
<min>-30</min>
<max>15</max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Elevator position normalized">
<input>fcs/elevator-pos-deg</input>
<domain>
<min>-30</min>
<max>15</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>
<gain>0.02</gain>
<range>
<min>-25</min>
<max>25</max>
</range>
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Control">
<input>-fcs/roll-trim-sum</input>
<gain>0.02</gain>
<range>
<min>-25</min>
<max>25</max>
</range>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Left Aileron position normalized">
<input>fcs/left-aileron-pos-deg</input>
<domain>
<min>-25</min>
<max>25</max>
</domain>
<range>
<min>-0.75</min>
<max>1</max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron position normalized">
<input>fcs/right-aileron-pos-deg</input>
<domain>
<min>-25</min>
<max>25</max>
</domain>
<range>
<min>-0.75</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>
<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>
</scheduled_gain>
<scheduled_gain name="Yaw Damper Beta">
<input>aero/beta-rad</input>
<table>
<independentVar lookup="row">velocities/ve-kts</independentVar>
<tableData>
30 0.00
60 0.00
</tableData>
</table>
</scheduled_gain>
<summer name="Yaw Damper Sum">
<input>fcs/yaw-damper-beta</input>
<input>fcs/yaw-damper-rate</input>
<clipto>
<min> -0.1 </min>
<max> 0.1 </max>
</clipto>
</summer>
<scheduled_gain name="Yaw Damper Final">
<input>fcs/yaw-damper-sum</input>
<table>
<independentVar lookup="row">velocities/ve-kts</independentVar>
<tableData>
30 0.0
31 1.0
</tableData>
</table>
</scheduled_gain>
<summer name="Rudder Sum">
<input>fcs/rudder-command-sum</input>
<input>fcs/yaw-damper-final</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>
<aerosurface_scale name="Rudder Control">
<input>fcs/rudder-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>40</position>
<time>40</time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="Flap position normalized">
<input>fcs/flap-pos-deg</input>
<domain>
<min>0</min>
<max>40</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>10</time>
</setting>
</traverse>
<output>gear/gear-pos-norm</output>
</kinematic>
</channel>
<channel name="Speedbrake">
<kinematic name="Speedbrake">
<input>fcs/speedbrake-cmd-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>2</time>
</setting>
</traverse>
<output>fcs/speedbrake-pos-norm</output>
</kinematic>
</channel>
</flight_control>
<aerodynamics>
<function name="aero/function/kCDge">
<description>Change_in_drag_due_to_ground_effect</description>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 0.4800
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
0.9000 1.0000
1.0000 1.0000
1.1000 1.0000
</tableData>
</table>
</function>
<function name="aero/function/kCLge">
<description>Change_in_lift_due_to_ground_effect</description>
<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>
</function>
<axis name="LIFT">
<function name="aero/force/Lift_gain">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value>0.250</value> <!-- down from 0.30 because that caused at high speed and altitude the AP to hold the nose down to prevent unintended climbing -->
</product>
</function>
<!--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>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 1.0000 9.0000 10.0000 40.0000
-0.0900 -0.2200 -0.2200 -0.1200 -0.1200 0.3200
0.0000 0.2500 0.2500 0.3500 0.3500 0.7500
0.0900 0.7300 0.7300 0.8300 0.8300 1.2300
0.1000 0.8300 0.8300 0.9300 0.9300 1.3300
0.1200 0.9200 0.9200 1.0200 1.0200 1.4200
0.1400 1.0200 1.0200 1.1200 1.1200 1.5200
0.1600 1.0800 1.0800 1.1800 1.1800 1.5800
0.1700 1.1300 1.1300 1.2300 1.2300 1.6300
0.1900 1.1900 1.1900 1.2900 1.2900 1.6900
0.2100 1.2500 1.2500 1.3500 1.3500 1.7700
0.2400 1.3500 1.3700 1.4700 1.4800 1.9300
0.2600 1.4400 1.4700 1.5700 1.6200 2.1200
0.2800 1.4700 1.5100 1.6100 1.7800 2.4000
0.3000 1.5000 1.5600 1.6600 1.9000 2.3000
0.3200 1.4700 1.6100 1.6000 1.7000 2.0300
0.3400 1.3500 1.5000 1.4100 1.5000 1.5300
0.3600 1.1500 1.2000 1.2000 1.2000 1.2000
</tableData>
</table>
</product>
</function-->
<function name="aero/force/Lift_alpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 1.0000 9.0000 10.0000 40.0000
-0.0900 -0.2200 -0.2200 -0.1200 -0.1200 0.2500
0.0000 0.2500 0.2500 0.3500 0.3500 0.7500
0.0900 0.7300 0.7300 0.8300 0.8300 1.2300
0.1000 0.8300 0.8300 0.9300 0.9300 1.3300
0.1200 0.9200 0.9200 1.0200 1.0200 1.4200
0.1400 1.0200 1.0200 1.1200 1.1200 1.5200
0.1600 1.0800 1.0800 1.1800 1.1800 1.5800
0.1700 1.1300 1.1300 1.2300 1.2300 1.6300
0.1900 1.1900 1.1900 1.2900 1.2900 1.6900
0.2100 1.2500 1.2500 1.3500 1.3500 1.7700
0.2400 1.3500 1.3700 1.4700 1.4800 1.9300
0.2600 1.4400 1.4700 1.5700 1.6200 2.1200
0.2800 1.4700 1.5100 1.6100 1.7800 2.4000
0.3000 1.5000 1.5600 1.6600 1.9000 2.3000
0.3200 1.4700 1.6100 1.6000 1.7000 2.0300
0.3400 1.3500 1.5000 1.4100 1.5000 1.5300
0.3600 1.1500 1.2000 1.2000 1.2000 1.2000
</tableData>
</table>
</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>0.1930</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>0.1930</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>-0.15</value>
</product>
</function>
</axis>
<axis name="DRAG">
<function name="aero/force/Drag_zero_lift">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value>0.016</value>
</product>
</function>
<!--function name="aero/coefficient/CDalpha">
<description>Drag_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 1.0000 25.0000 40.0000
-0.0873 0.0041 0.0000 0.0005 0.0014
-0.0698 0.0013 0.0004 0.0025 0.0041
-0.0524 0.0001 0.0023 0.0059 0.0084
-0.0349 0.0003 0.0057 0.0108 0.0141
-0.0175 0.0020 0.0105 0.0172 0.0212
0.0000 0.0052 0.0168 0.0251 0.0399
0.0175 0.0099 0.0248 0.0346 0.0502
0.0349 0.0162 0.0342 0.0457 0.0621
0.0524 0.0240 0.0452 0.0583 0.0755
0.0698 0.0334 0.0577 0.0724 0.0904
0.0873 0.0442 0.0718 0.0881 0.1068
0.1047 0.0566 0.0874 0.1053 0.1248
0.1222 0.0706 0.1045 0.1240 0.1443
0.1396 0.0860 0.1232 0.1442 0.1654
0.1571 0.0962 0.1353 0.1573 0.1790
0.1745 0.1069 0.1479 0.1708 0.1930
0.1920 0.1180 0.1610 0.1849 0.2075
0.2094 0.1298 0.1746 0.1995 0.2226
0.2269 0.1424 0.1892 0.2151 0.2386
0.2443 0.1565 0.2054 0.2323 0.2564
0.2618 0.1727 0.2240 0.2521 0.2767
0.2793 0.1782 0.2302 0.2587 0.2835
0.2967 0.1716 0.2227 0.2507 0.2753
0.3142 0.1618 0.2115 0.2388 0.2631
0.3316 0.1475 0.1951 0.2214 0.2451
0.3491 0.1097 0.1512 0.1744 0.1966
</tableData>
</table>
</product>
</function-->
<function name="aero/force/Drag_alpha">
<description>Drag_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 1.0000 25.0000 40.0000
-0.0873 0.0041 0.0000 0.0005 0.0014
-0.0698 0.0013 0.0004 0.0025 0.0041
-0.0524 0.0001 0.0023 0.0059 0.0084
-0.0349 0.0003 0.0057 0.0108 0.0141
-0.0175 0.0020 0.0105 0.0172 0.0212
0.0000 0.0052 0.0168 0.0251 0.0399
0.0175 0.0099 0.0248 0.0346 0.0502
0.0349 0.0162 0.0342 0.0457 0.0621
0.0524 0.0240 0.0452 0.0583 0.0755
0.0698 0.0334 0.0577 0.0724 0.0904
0.0873 0.0442 0.0718 0.0881 0.1068
0.1047 0.0566 0.0874 0.1053 0.1248
0.1222 0.0706 0.1045 0.1240 0.1443
0.1396 0.0860 0.1232 0.1442 0.1654
0.1571 0.0962 0.1353 0.1573 0.1790
0.1745 0.1069 0.1479 0.1708 0.1930
0.1920 0.1180 0.1610 0.1849 0.2075
0.2094 0.1298 0.1746 0.1995 0.2226
0.2269 0.1424 0.1892 0.2151 0.2386
0.2443 0.1565 0.2054 0.2323 0.2564
0.2618 0.1727 0.2240 0.2521 0.2767
0.2793 0.1782 0.2302 0.2587 0.2835
0.2967 0.1716 0.2227 0.2507 0.2753
0.3142 0.1618 0.2115 0.2388 0.2631
0.3316 0.1475 0.1951 0.2214 0.2451
0.3491 0.1097 0.1512 0.1744 0.1966
</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/mag-elevator-pos-rad</property>
<value>0.0500</value>
</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>0.055</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>
<property>aero/mag-beta-rad</property>
<value>0.2000</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>
<property>aero/mag-beta-rad</property>
<value>0.2000</value>
</product>
</function>
<!--function name="aero/coefficient/CDgear">
<description>Drag_due_to_landing_gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>gear/gear-pos-norm</property>
<value>0.0400</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>0.04</value>
</product>
</function>
<!--function name="aero/coefficient/CDspeedbrake">
<description>Drag_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.0400</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>0.04</value>
</product>
</function>
<!--function name="aero/coefficient/CDo">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value>0.016</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>
</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>
<table>
<independentVar>aero/beta-rad</independentVar>
<tableData>
-0.3500 0.5000
0.0000 0.0000
0.3500 -0.5000
</tableData>
</table>
</product>
</function -->
<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/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>
<table>
<independentVar>aero/beta-rad</independentVar>
<tableData>
-0.3500 0.0100
0.0000 0.0000
0.3500 -0.0100
</tableData>
</table>
</product>
</function-->
<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/coefficient/Clp">
<description>Roll_moment_due_to_roll_rate_(roll_damping)</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>-0.5000</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/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>0.0050</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>0.005</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>
<!- value>0.2000</value -> <!- Excesive roll !!! ->
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.0 0.100
2.0 0.033
</tableData>
</table>
</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>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.0 0.100
2.0 0.033
</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>0.0050</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>0.005</value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/moment/Pitch_zero_alpha_and_flaps">
<description>Pitching_moment_at_zero_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 0.0000
40.0000 -0.1000
</tableData>
</table>
</product>
</function>
<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>-4.0000</value> -->
<value>-0.6</value>
</product>
</function>
<function name="aero/moment/Pitch_elevator">
<description>Pitch_moment_due_to_elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elevator-pos-rad</property>
<!-- <value>-1.5000</value> Excesive Pitch -->
<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>-10.0000</value-->
<value>-10</value>
</product>
</function>
<function name="aero/moment/Pitch_alpha_rate">
<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>-12.0000</value-->
<value>-12</value>
</product>
</function>
</axis>
<axis name="YAW">
<!--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>-0.0400</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/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>0.2000</value>
</product>
</function-->
<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/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>-0.5000</value> Excesive Yaw->
<value>-0.3</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>-0.2</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>
<force name="tractor" frame="BODY">
<location unit="IN">
<x> -980.19 </x>
<y> 0.00 </y>
<z> -65.00 </z>
</location>
<direction>
<x>1</x>
<y>0</y>
<z>0</z>
</direction>
</force>
</external_reactions>
</fdm_config>
Reference in a new issue Copy permalink