2767 lines
121 KiB
XML
2767 lines
121 KiB
XML
<?xml version="1.0"?>
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<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
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<fdm_config name="F-22 Cobra Research" version="2.0" release="EXPERIMENTAL"
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xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
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xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
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<fileheader>
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<author>Brian Mills </author>
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<license
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licenseName="GPL (General Public License)"
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licenseURL="http://www.gnu.org/licenses/gpl.html"/>
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<filecreationdate>2009-05-24</filecreationdate>
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<version>$Revision: 1.38 $</version>
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<description>Models an F-22A Raptor</description>
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<note>
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This model was created using data that is, or has been, publically
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available by means of technical reports, textbooks, image graphs or
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published code. This aircraft description file is in no way related
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to the manufacturer of the real aircraft.
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Neither the name of (any of) the authors nor the names of (any of) the
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manufacturers may be used to endorse or promote products derived from
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this file.
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The data is provided ''as is'' and any express or implied
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warranties, including, but not limitted to the implied warranties of
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merchantability and fitness for a particular purpose are disclaimed.
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</note>
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</fileheader>
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<metrics>
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<wingarea unit="FT2"> 840.0 </wingarea>
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<wingspan unit="FT"> 44.49 </wingspan>
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<chord unit="FT"> 23.06 </chord>
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<htailarea unit="FT2"> 238.9 </htailarea>
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<htailarm unit="FT"> 18.66 </htailarm>
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<vtailarea unit="FT2"> 158.2 </vtailarea>
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<vtailarm unit="FT"> 0 </vtailarm>
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<location name="AERORP" unit="IN">
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<x> 417.6 </x>
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<y> 0 </y>
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<z> 0 </z>
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</location>
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<location name="EYEPOINT" unit="IN">
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<x> 148.8 </x>
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<y> 0 </y>
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<z> 38 </z>
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</location>
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<location name="VRP" unit="IN">
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<x> 100 </x>
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<y> 0 </y>
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<z> 0 </z>
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</location>
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</metrics>
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<mass_balance negated_crossproduct_inertia="true">
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<ixx unit="SLUG*FT2"> 56005 </ixx>
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<iyy unit="SLUG*FT2"> 280766 </iyy>
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<izz unit="SLUG*FT2"> 354090 </izz>
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<ixz unit="SLUG*FT2"> 713 </ixz>
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<emptywt unit="LBS"> 43430 </emptywt>
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<location name="CG" unit="IN">
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<x> 445.7 </x>
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<y> 0 </y>
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<z> -18.6 </z>
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</location>
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<pointmass name="Pilot">
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<weight unit="LBS"> 230 </weight>
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<location unit="IN">
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<x> 148.8 </x>
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<y> 0 </y>
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<z> 20 </z>
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</location>
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</pointmass>
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</mass_balance>
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<ground_reactions>
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<contact type="BOGEY" name="NOSE_LG">
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<location unit="IN">
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<x> 96.7 </x>
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<y> 0 </y>
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<z> -89.3 </z>
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</location>
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<static_friction> 0.8 </static_friction>
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<dynamic_friction> 0.5 </dynamic_friction>
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<rolling_friction> 0.02 </rolling_friction>
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<spring_coeff unit="LBS/FT"> 18603.4 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 6201.1 </damping_coeff>
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<max_steer unit="DEG"> 80 </max_steer>
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<brake_group> NONE </brake_group>
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<retractable>1</retractable>
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</contact>
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<contact type="BOGEY" name="LEFT_MLG">
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<location unit="IN">
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<x> 468.8 </x>
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<y> -48 </y>
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<z> -89.3 </z>
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</location>
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<static_friction> 0.8 </static_friction>
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<dynamic_friction> 0.5 </dynamic_friction>
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<rolling_friction> 0.02 </rolling_friction>
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<spring_coeff unit="LBS/FT"> 82011.2 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 22402.2 </damping_coeff>
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<max_steer unit="DEG"> 0.0 </max_steer>
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<brake_group> LEFT </brake_group>
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<retractable>1</retractable>
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</contact>
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<contact type="BOGEY" name="RIGHT_MLG">
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<location unit="IN">
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<x> 468.8 </x>
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<y> 48 </y>
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<z> -89.3 </z>
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</location>
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<static_friction> 0.8 </static_friction>
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<dynamic_friction> 0.5 </dynamic_friction>
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<rolling_friction> 0.02 </rolling_friction>
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<spring_coeff unit="LBS/FT"> 82011.2 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 22402.2 </damping_coeff>
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<max_steer unit="DEG"> 0.0 </max_steer>
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<brake_group> RIGHT </brake_group>
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<retractable>1</retractable>
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</contact>
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</ground_reactions>
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<propulsion>
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<engine file="F119-PW-1">
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<feed>0</feed>
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<feed>1</feed>
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<thruster file="direct">
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<location unit="IN">
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<x> 684.131 </x>
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<y>-20 </y>
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<z> 0 </z>
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</location>
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<orient unit="DEG">
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<roll> 0.0 </roll>
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<pitch> 0.0 </pitch>
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<yaw> 0.0 </yaw>
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</orient>
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</thruster>
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</engine>
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<engine file="F119-PW-1">
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<feed>0</feed>
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<feed>1</feed>
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<thruster file="direct">
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<location unit="IN">
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<x> 684.131 </x>
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<y> 20 </y>
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<z> 0 </z>
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</location>
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<orient unit="DEG">
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<roll> 0.0 </roll>
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<pitch> 0.0 </pitch>
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<yaw> 0.0 </yaw>
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</orient>
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</thruster>
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</engine>
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<tank type="FUEL">
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<location unit="IN">
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<x> 446.478 </x>
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<y> -36 </y>
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<z> -18.6033 </z>
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</location>
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<capacity unit="LBS"> 9350 </capacity>
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<contents unit="LBS"> 9350 </contents>
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</tank>
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<tank type="FUEL">
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<location unit="IN">
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<x> 446.478 </x>
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<y> 36 </y>
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<z> -18.6033 </z>
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</location>
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<capacity unit="LBS"> 9350 </capacity>
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<contents unit="LBS"> 9350 </contents>
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</tank>
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</propulsion>
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<flight_control name="F-22 FC">
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<property>fcs/tvc-cmd-norm</property>
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<!-- Declare some interface properties -->
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<!-- <property>fcs/alpha-norm</property>
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<property>fcs/tvc-pos-norm</property>
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<property>fcs/tvc-pos-rad</property>
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<property>fcs/thrust-norm</property>
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<property>fcs/lef-pos-rad</property>
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<property>fcs/lef-pos-norm</property>
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<property>fcs/throttle-override</property>
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<property>fcs/speedbrake-aileron</property>
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<property>fcs/speedbrake-aileron-right</property>
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<property>fcs/speedbrake-rudder</property>
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<property>fcs/speedbrake-flap</property>
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<property>fcs/yaw-rate-integrator</property>
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<property>fcs/pitch-rate-integrator</property>
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<property>fcs/tvc-inhibit</property> -->
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<channel name="Lateral">
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<!-- Normalize the u-velocity to m/s-->
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<pure_gain name="fcs/u-velocity-norm">
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<input>velocities/u-fps</input>
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<gain>0.3048</gain>
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</pure_gain>
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<summer name="fcs/aileron-cmd-limiter">
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<input>fcs/aileron-cmd-norm</input>
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<input>fcs/roll-trim-cmd-norm</input>
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<clipto>
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<min>-1</min>
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<max>1</max>
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</clipto>
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</summer>
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<!-- Stick filter -->
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<lag_filter name="fcs/roll-cmd-filter">
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<input>fcs/aileron-cmd-limiter</input>
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<c1>10</c1>
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</lag_filter>
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<!-- Limit roll rate command in radians based on altitude, mach and AoA-->
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<fcs_function name="fcs/roll-cmd-limit">
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<function>
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<table>
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<independentVar lookup="column">velocities/mach</independentVar>
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<independentVar lookup="row">aero/alpha-deg</independentVar>
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<independentVar lookup="table">position/h-sl-ft</independentVar>
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<tableData breakPoint="0">
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0 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6
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-90 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6
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-25 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6
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-20 0.6 0.85 1 1 1 1 1 1 1
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-15 0.6 0.85 1.5 1.5 1.5 1.5 1.5 1.5 1.5
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-10 0.6 1 2.5 3.14 3.14 3.14 3.14 2.617 2.1
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0 0.6 1.5 2.5 3.66 4 4 3.14 2.617 2.1
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10 0.6 1 2.5 3.14 3.14 3.14 3.14 2.617 2.1
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15 0.6 0.85 2.5 2.617 2.617 2.617 2.617 2.617 2.1
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20 0.6 0.85 2.1 2.1 2.1 2.1 2.1 2.1 2.1
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25 0.6 0.85 1.5 1.5 1.5 1.5 1.5 1.5 1.5
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30 0.6 0.85 1.3 1.3 1.3 1.3 1.3 1.3 1.3
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35 0.6 0.85 1 1 1 1 1 1 1
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40 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
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45 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
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180 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
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</tableData>
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<tableData breakPoint="30000">
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0 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6
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-90 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6
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-25 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6
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-20 0.6 0.85 1 1 1 1 1 1 1
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-15 0.6 0.85 1.5 1.5 1.5 1.5 1.5 1.5 1.5
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-10 0.6 0.85 2.5 3.14 3.14 3.14 3.14 2.617 2.1
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0 0.6 0.85 2.5 3.66 4 4 3.14 2.617 2.1
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10 0.6 0.85 2.5 3.14 3.14 3.14 3.14 2.617 2.1
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15 0.6 0.85 2.5 2.617 2.617 2.617 2.617 2.617 2.1
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20 0.6 0.85 2.1 2.1 2.1 2.1 2.1 2.1 2.1
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25 0.6 0.85 1.5 1.5 1.5 1.5 1.5 1.5 1.5
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30 0.6 0.85 1.3 1.3 1.3 1.3 1.3 1.3 1.3
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35 0.6 0.85 1 1 1 1 1 1 1
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40 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
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45 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
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180 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
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</tableData>
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<tableData breakPoint="70000">
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0 0.2 0.4 0.6 0.8 1.0 1.2 1.4 1.6
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-90 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6
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-25 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6 0.6
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-20 0.6 0.85 1 1 1 1 1 1 1
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-15 0.6 0.85 1 1.25 1.5 1.5 1.5 1.5 1.5
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-10 0.6 0.85 1.5 1.5 2 2.25 2.25 2.25 2
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0 0.6 0.85 1.5 2 2.5 2.5 2.75 2.75 2.5
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10 0.6 0.85 1.5 1.5 2 2.25 2.25 2.25 2
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15 0.6 0.85 1.5 2 2 2 2 2 2
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20 0.6 0.85 1 1.25 1.5 2 2 2 2
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25 0.6 0.85 1 1.25 1.5 1.5 1.5 1.5 1.5
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30 0.6 0.85 1 1 1.3 1.3 1.3 1.3 1.3
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35 0.6 0.85 1 1 1 1 1 1 1
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40 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
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45 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
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180 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4 0.4
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</tableData>
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</table>
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</function>
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</fcs_function>
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<!-- Calculate the normalized commanded roll rate absolutely limited to +230 deg/s -230 deg/s-->
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<pure_gain name="fcs/roll-rate-cmd">
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<input>fcs/roll-cmd-filter</input>
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<gain>fcs/roll-cmd-limit</gain>
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<clipto>
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<min>-4</min>
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<max>4</max>
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</clipto>
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</pure_gain>
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<deadband name="fcs/roll-windup-trigger">
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<input>fcs/roll-rate-integrator</input>
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<width>8</width>
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<clipto>
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<min>-4</min>
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<max>4</max>
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</clipto>
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</deadband>
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<summer name="fcs/roll-rate-error">
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<input>fcs/roll-rate-cmd</input>
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<input>-velocities/p-aero-rad_sec</input>
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<input>-fcs/roll-windup-trigger</input>
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</summer>
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<integrator name="fcs/roll-rate-integrator">
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<!--trigger>fcs/aileron-int-trigger</trigger-->
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<input>fcs/roll-rate-error</input>
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<c1> 1 </c1>
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<clipto>
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<min>-4</min>
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<max>4</max>
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</clipto>
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</integrator>
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<!-- Normalize the v-velocity to m/s-->
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<pure_gain name="fcs/v-velocity-norm">
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<input>velocities/v-fps</input>
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<gain>0.3048</gain>
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</pure_gain>
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<pure_gain name="fcs/rudder-cmd-limiter">
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<input>fcs/rudder-cmd-norm</input>
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<gain> 1.0 </gain>
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<clipto>
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<min>-1</min>
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<max>1</max>
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</clipto>
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</pure_gain>
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<!-- Rudder pedal filter -->
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<lag_filter name="fcs/rudder-cmd-filter">
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<input>fcs/rudder-cmd-limiter</input>
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<c1>10</c1>
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</lag_filter>
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<!-- Limit yaw rate command in radians based on mach and altitude -->
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<fcs_function name="fcs/yaw-rate-limit">
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<function>
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<table>
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<independentVar lookup="row">velocities/mach</independentVar>
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<independentVar lookup="column">position/h-sl-ft</independentVar>
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<tableData>
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|
0 36000
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|
0 -0.436 -0.436
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0.4 -0.349 -0.349
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0.8 -0.1745 -0.1745
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1.0 -0.1 -0.1
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2.0 -0.1 -0.1
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</tableData>
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</table>
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</function>
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</fcs_function>
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<pure_gain name="fcs/yaw-rate-cmd">
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<input>fcs/rudder-cmd-filter</input>
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<gain>fcs/yaw-rate-limit</gain>
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</pure_gain>
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<!-- washout filter to fullfill handling qualities-->
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<washout_filter name="fcs/yaw-rate-filter">
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<input>velocities/r-aero-rad_sec</input>
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<c1> 1.2 </c1>
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</washout_filter>
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|
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<deadband name="fcs/yaw-windup-trigger">
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<input>fcs/yaw-rate-integrator</input>
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<width>0.872</width>
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|
<clipto>
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<min>-0.436</min>
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|
<max>0.436</max>
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</clipto>
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</deadband>
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|
|
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<summer name="fcs/yaw-rate-error">
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<input> -fcs/yaw-rate-filter </input>
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<input> -fcs/yaw-windup-trigger </input>
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<input> fcs/yaw-rate-cmd </input>
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</summer>
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|
|
|
<integrator name="fcs/yaw-rate-integrator">
|
|
<!--trigger>fcs/rudder-int-trigger</trigger-->
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|
<input>fcs/yaw-rate-error</input>
|
|
<c1> 1 </c1>
|
|
<clipto>
|
|
<min>-0.436</min>
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|
<max>0.436</max>
|
|
</clipto>
|
|
<output>fcs/yaw-rate-integrator</output>
|
|
</integrator>
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|
|
|
<!-- if yaw rate exceeds limits based on rate and mach, then apply opposite rudder-->
|
|
<fcs_function name="fcs/yaw-rate-override">
|
|
<function>
|
|
<table>
|
|
<independentVar lookup="row">velocities/r-aero-rad_sec</independentVar>
|
|
<independentVar lookup="column">velocities/mach</independentVar>
|
|
<tableData>
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|
0 0.4 0.8 1.0 2.0
|
|
-0.440 0.872 0.7 0.35 0.2 0.2
|
|
-0.436 0 0.7 0.35 0.2 0.2
|
|
-0.360 0 0.7 0.35 0.2 0.2
|
|
-0.349 0 0 0.35 0.2 0.2
|
|
-0.180 0 0 0.35 0.2 0.2
|
|
-0.1745 0 0 0 0.2 0.2
|
|
-0.11 0 0 0 0.2 0.2
|
|
-0.1 0 0 0 0 0
|
|
0 0 0 0 0 0
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|
0.1 0 0 0 0 0
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|
0.11 0 0 0 -0.2 -0.2
|
|
0.1745 0 0 0 -0.2 -0.2
|
|
0.18 0 0 -0.35 -0.2 -0.2
|
|
0.349 0 0 -0.35 -0.2 -0.2
|
|
0.36 0 -0.7 -0.35 -0.2 -0.2
|
|
0.436 0 -0.7 -0.35 -0.2 -0.2
|
|
0.440 -0.872 -0.7 -0.35 -0.2 -0.2
|
|
</tableData>
|
|
</table>
|
|
</function>
|
|
</fcs_function>
|
|
|
|
<summer name="fcs/yaw-cmd-summer">
|
|
<input>fcs/yaw-rate-integrator</input>
|
|
<input>fcs/yaw-rate-override</input>
|
|
</summer>
|
|
|
|
<!-- LQR Tracker Integral aileron roll-rate control-->
|
|
<fcs_function name="fcs/roll-cmd">
|
|
<function>
|
|
<sum>
|
|
<product>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 33000 50000
|
|
160 0.5 0.35 0.3
|
|
270 0.5 0.35 0.3
|
|
400 0.45 0.4 0.3
|
|
500 0.45 0.4 0.35
|
|
580 0.5 0.45 0.35
|
|
1000 0.5 0.45 0.4
|
|
</tableData>
|
|
</table>
|
|
<property> fcs/roll-rate-integrator </property>
|
|
<value> -1 </value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 33000 50000
|
|
160 -28.4059 -31.1627 -31.1627
|
|
270 -30.9146 -32.6575 -32.6575
|
|
330 -35.9146 -32.6575 -32.6575
|
|
400 -44.4687 -38.7651 -38.7651
|
|
580 -44.2746 -36.5662 -36.5662
|
|
700 -39.0735 -34.9842 -34.9842
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
<product>
|
|
<property> fcs/v-velocity-norm </property>
|
|
<value> 0 </value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 33000 50000
|
|
160 -0.0494 -0.0266 -0.0266
|
|
270 0.0067 -0.0160 -0.0160
|
|
330 0.0067 -0.0160 -0.0160
|
|
400 -0.1082 -0.0108 -0.0108
|
|
580 -0.0104 -0.0091 -0.0091
|
|
700 -0.0095 -0.0118 -0.0118
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
<product>
|
|
<!--table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 33000 50000
|
|
160 1 1.5 2
|
|
270 1 1.35 1.75
|
|
400 1 1.2 1.5
|
|
500 1.0 1.1 1.0
|
|
580 1.0 1.0 1.0
|
|
1000 1.0 1.0 1.0
|
|
</tableData>
|
|
</table-->
|
|
<property>velocities/p-aero-rad_sec</property>
|
|
<value>-.35</value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 33000 50000
|
|
160 11.7952 13.4573 13.4573
|
|
270 11.9041 13.1381 13.1381
|
|
330 11.9041 13.1381 13.1381
|
|
400 12.0644 10.6808 10.6808
|
|
580 11.0366 10.7511 10.7511
|
|
700 9.3909 10.8556 10.8556
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</sum>
|
|
<!--table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-1 -0.25 0 0.25 0.5 1 2 3
|
|
160 1.5 1.25 1 1.25 1.5 2 2.5 3
|
|
270 1.5 1.25 1 1.25 1.5 2 2.5 3
|
|
400 1.5 1.25 1 1.25 1.5 2 2.5 3
|
|
500 1.5 1.15 1 1.15 1.35 2 2.5 3
|
|
580 1.5 1.15 1 1.15 1.35 2 2.5 3
|
|
1000 1.5 1.15 1 1.15 1.35 2 2.5 3
|
|
|
|
</tableData>
|
|
</table-->
|
|
</function>
|
|
<clipto>
|
|
<min>-5</min>
|
|
<max>5</max>
|
|
</clipto>
|
|
</fcs_function>
|
|
|
|
<aerosurface_scale name="fcs/roll-reg-scale">
|
|
<input> fcs/roll-cmd </input>
|
|
<domain>
|
|
<min> -5 </min>
|
|
<max> 5 </max>
|
|
</domain>
|
|
<range>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</range>
|
|
</aerosurface_scale >
|
|
|
|
<actuator name="fcs/aileron-act">
|
|
<input> fcs/roll-reg-scale</input>
|
|
<lag> 0.00 </lag>
|
|
<rate_limit> 2.29 </rate_limit>
|
|
<clipto>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</clipto>
|
|
</actuator>
|
|
|
|
<summer name="fcs/left-aileron-out">
|
|
<input>fcs/aileron-act</input>
|
|
<input>fcs/speedbrake-aileron</input>
|
|
<clipto>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</clipto>
|
|
<output>fcs/left-aileron-pos-norm</output>
|
|
</summer>
|
|
|
|
<aerosurface_scale name="fcs/left-aileron-control">
|
|
<input>fcs/aileron-act</input>
|
|
<range>
|
|
<min>-0.436</min>
|
|
<max>0.436</max>
|
|
</range>
|
|
<output>fcs/left-aileron-pos-rad</output>
|
|
</aerosurface_scale>
|
|
|
|
<pure_gain name="fcs/left-aileron-neg">
|
|
<input>fcs/aileron-act</input>
|
|
<gain>-1</gain>
|
|
</pure_gain>
|
|
|
|
<summer name="fcs/right-aileron-out">
|
|
<input>fcs/left-aileron-neg</input>
|
|
<input>fcs/speedbrake-aileron-right</input>
|
|
<clipto>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</clipto>
|
|
<output>fcs/right-aileron-pos-norm</output>
|
|
</summer>
|
|
|
|
<aerosurface_scale name="fcs/right-aileron-control">
|
|
<input>fcs/left-aileron-neg</input>
|
|
<range>
|
|
<min>-0.436</min>
|
|
<max>0.436</max>
|
|
</range>
|
|
<output>fcs/right-aileron-pos-rad</output>
|
|
</aerosurface_scale>
|
|
|
|
<!-- LQR Tracker Integral rudder yaw-rate control-->
|
|
<fcs_function name="fcs/yaw-cmd">
|
|
<function>
|
|
<product>
|
|
<sum>
|
|
<product>
|
|
<property>fcs/yaw-cmd-summer</property>
|
|
<value>-0.2</value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 33000 50000
|
|
160 22.1027 22.1741 22.1741
|
|
270 22.1775 15.7518 15.7518
|
|
400 14.0894 14.0894 14.0894
|
|
580 12.8629 12.8629 12.8629
|
|
700 14.8347 12.8631 12.8631
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
<product>
|
|
<property>fcs/yaw-rate-filter</property>
|
|
<value>-0.2</value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 33000 50000
|
|
160 -21.4844 -29.9948 -29.9948
|
|
270 -19.5573 -17.5259 -17.5259
|
|
400 -13.6930 -13.6930 -13.6930
|
|
580 -9.6423 -9.6423 -9.6423
|
|
700 -7.7903 -6.1197 -6.1197
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</sum>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 33000 50000
|
|
160 1 1.2 1.2
|
|
270 1 1.1 1.1
|
|
400 0.5 0.55 0.6
|
|
580 0.3 0.35 0.4
|
|
700 0.2 0.25 0.3
|
|
</tableData>
|
|
</table>
|
|
<table>
|
|
<independentVar lookup="row">aero/alpha-deg</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 33000 50000
|
|
-60 3 3.5 4
|
|
-40 2 2.5 3
|
|
-20 1.5 1.75 2
|
|
0 0.7 0.8 0.9
|
|
20 1.75 2 2.5
|
|
40 2.5 3 3.5
|
|
60 3 3.5 4
|
|
80 3.5 4 5
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<clipto>
|
|
<min>-5</min>
|
|
<max>5</max>
|
|
</clipto>
|
|
</fcs_function>
|
|
|
|
<aerosurface_scale name="fcs/yaw-reg-scale">
|
|
<input> fcs/yaw-cmd </input>
|
|
<domain>
|
|
<min> -5 </min>
|
|
<max> 5 </max>
|
|
</domain>
|
|
<range>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</range>
|
|
</aerosurface_scale >
|
|
|
|
<actuator name="fcs/rudder-act">
|
|
<input> fcs/yaw-reg-scale</input>
|
|
<lag> 0 </lag>
|
|
<rate_limit> 2.673 </rate_limit>
|
|
|
|
<clipto>
|
|
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</clipto>
|
|
</actuator>
|
|
|
|
<summer name="fcs/rudder-pos-out">
|
|
<input>fcs/rudder-act</input>
|
|
<input>fcs/speedbrake-rudder</input>
|
|
<clipto>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</clipto>
|
|
<output>fcs/rudder-pos-norm</output>
|
|
</summer>
|
|
|
|
<aerosurface_scale name="fcs/rudder-position">
|
|
<input>fcs/rudder-act</input>
|
|
<range>
|
|
<min>-0.5236</min>
|
|
<max>0.5236</max>
|
|
</range>
|
|
<output>fcs/rudder-pos-rad</output>
|
|
</aerosurface_scale>
|
|
</channel>
|
|
|
|
<channel name="Pitch">
|
|
|
|
<!--
|
|
- accelerations/n-pilot-z-norm has the disadvantage that it
|
|
- has an offset of 1G when positioned horizontal (and -1G
|
|
- when upside down). To calculate the difference between the
|
|
- commanded pitch-rate and actual pitch-rate this offset has
|
|
- to be eliminated. The following function calculates an offset
|
|
- to compensate for the earth's gravity.
|
|
-->
|
|
<fcs_function name="fcs/n-pilot-z-correction">
|
|
<function>
|
|
<product>
|
|
<cos>
|
|
<property>attitude/pitch-rad</property>
|
|
</cos>
|
|
<cos>
|
|
<property>attitude/roll-rad</property>
|
|
</cos>
|
|
</product>
|
|
</function>
|
|
</fcs_function>
|
|
|
|
<summer name="fcs/g-load-corrected">
|
|
<input>accelerations/n-pilot-z-norm</input>
|
|
<input>-fcs/n-pilot-z-correction</input>
|
|
</summer>
|
|
|
|
<pure_gain name="fcs/g-load-norm">
|
|
<input>fcs/g-load-corrected</input>
|
|
<gain>-1.0</gain>
|
|
</pure_gain>
|
|
|
|
<!-- Pilot stick filter -->
|
|
<lag_filter name="fcs/stick-filter">
|
|
<input>fcs/elevator-cmd-norm</input>
|
|
<c1>10</c1>
|
|
</lag_filter>
|
|
|
|
<!-- Do not allow TVC to operate when gear is down! -->
|
|
<switch name="fcs/tvc-inhibit">
|
|
<default value="1"/>
|
|
<test logic="AND" value="0">
|
|
gear/gear-pos-norm gt 0
|
|
</test>
|
|
<output>fcs/tvc-inhibit</output>
|
|
</switch>
|
|
|
|
<summer name="fcs/elevator-cmd-limiter">
|
|
<input>fcs/stick-filter</input>
|
|
<input>fcs/pitch-trim-cmd-norm</input>
|
|
<clipto>
|
|
<min>-1</min>
|
|
<max>0.6</max>
|
|
</clipto>
|
|
</summer>
|
|
|
|
<!-- Limit pitch rate command based on altitude and mach. Max of +50/-30 deg/sec command -->
|
|
<fcs_function name="fcs/pitch-cmd-limiter">
|
|
<function>
|
|
<table>
|
|
<independentVar lookup="row">velocities/mach</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
0 30000 60000
|
|
0 0.7 0.5236 0.349
|
|
0.2 0.8727 0.5236 0.349
|
|
0.4 0.8727 0.5236 0.349
|
|
0.6 0.8727 0.7 0.349
|
|
0.8 0.8727 0.7 0.349
|
|
1.0 0.7845 0.7 0.4363
|
|
1.2 0.611 0.611 0.4363
|
|
1.4 0.611 0.5236 0.349
|
|
1.6 0.5236 0.4363 0.349
|
|
1.8 0.4363 0.4363 0.349
|
|
2.0 0.349 0.349 0.349
|
|
</tableData>
|
|
</table>
|
|
</function>
|
|
</fcs_function>
|
|
|
|
<pure_gain name="fcs/pitch-rate-cmd">
|
|
<input>fcs/elevator-cmd-limiter</input>
|
|
<gain>-fcs/pitch-cmd-limiter</gain>
|
|
</pure_gain>
|
|
|
|
<!-- G-limiter based on mach. +9.5/-3.5 G limit. -->
|
|
<fcs_function name="fcs/pitch-cmd-g-limiter">
|
|
<function>
|
|
<table>
|
|
<independentVar lookup="column">velocities/mach</independentVar>
|
|
<independentVar lookup="row">fcs/g-load-norm</independentVar>
|
|
<tableData>
|
|
0 0.4 0.8 1.0 1.2 1.4 1.6 1.8 2.0
|
|
-3.75 0 0 0 0 0 0 0 0 0
|
|
-3.5 1 1 1 1 0 0 0 0 0
|
|
-3.25 1 1 1 1 1 1 0 0 0
|
|
-3.0 1 1 1 1 1 1 1 1 1
|
|
0 1 1 1 1 1 1 1 1 1
|
|
7 1 1 1 1 1 1 1 1 1
|
|
7.25 1 1 1 1 1 -0.1 -0.1 -0.1 -0.1
|
|
7.5 1 1 1 1 1 -0.1 -0.1 -0.1 -0.1
|
|
7.75 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1
|
|
8.0 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1
|
|
8.25 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1
|
|
8.5 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1
|
|
8.75 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1
|
|
9.0 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1
|
|
9.25 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1
|
|
9.5 1 1 1 1 -0.1 -0.1 -0.1 -0.1 -0.1
|
|
9.75 -0.1 -0.1 -0.1 -0.1 -0.1 -0.1 0 0 0
|
|
10.0 -1 -1 -1 -1 -1 -1 -1 -1 -1
|
|
</tableData>
|
|
</table>
|
|
</function>
|
|
</fcs_function>
|
|
|
|
<pure_gain name="fcs/g-limiter">
|
|
<input>fcs/pitch-rate-cmd</input>
|
|
<gain>fcs/pitch-cmd-g-limiter</gain>
|
|
<clipto>
|
|
<min>-0.5236</min>
|
|
<max>0.8727</max>
|
|
</clipto>
|
|
</pure_gain>
|
|
|
|
<!-- Limit pitch rate command when gear is down-->
|
|
<switch name="fcs/gear-down-q-limit">
|
|
<default value="1"/>
|
|
<test logic="AND" value=".3">
|
|
gear/gear-pos-norm gt 0
|
|
</test>
|
|
</switch>
|
|
|
|
<pure_gain name="fcs/q-gear-down-limiter">
|
|
<input>fcs/g-limiter</input>
|
|
<gain>fcs/gear-down-q-limit</gain>
|
|
<clipto>
|
|
<min>-0.5236</min>
|
|
<max>0.8727</max>
|
|
</clipto>
|
|
</pure_gain>
|
|
|
|
<deadband name="fcs/pitch-windup-trigger">
|
|
<input>fcs/pitch-rate-integrator</input>
|
|
<width>1.4</width>
|
|
<clipto>
|
|
<min>-0.5236</min>
|
|
<max>0.8727</max>
|
|
</clipto>
|
|
</deadband>
|
|
|
|
<summer name="fcs/pitch-rate-error">
|
|
<input>fcs/q-gear-down-limiter</input>
|
|
<input>-velocities/q-aero-rad_sec</input>
|
|
<input>-fcs/pitch-windup-trigger</input>
|
|
</summer>
|
|
|
|
<integrator name="fcs/pitch-rate-integrator">
|
|
<!--trigger>fcs/pitch-int-trigger</trigger-->
|
|
<input>fcs/pitch-rate-error</input>
|
|
<c1> 1 </c1>
|
|
<clipto>
|
|
<min>-0.5236</min>
|
|
<max>0.8727</max>
|
|
</clipto>
|
|
<output>fcs/pitch-rate-integrator</output>
|
|
</integrator>
|
|
|
|
<summer name="fcs/pitch-cmd-summer">
|
|
<input>fcs/pitch-rate-integrator</input>
|
|
<!--input>fcs/pitch-rate-override</input-->
|
|
</summer>
|
|
|
|
<!-- Normalize the w-velocity to m/s -->
|
|
<pure_gain name="fcs/w-velocity-norm">
|
|
<input>velocities/w-fps</input>
|
|
<gain>0.3048</gain>
|
|
</pure_gain>
|
|
|
|
<!-- LQR Tracker Integral elevator pitch rate controller-->
|
|
<fcs_function name="fcs/el-pitch-cmd">
|
|
<function>
|
|
<sum>
|
|
<product>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<tableData>
|
|
19 25 35
|
|
90 1 1 1
|
|
180 1 1 1
|
|
200 1 1 1
|
|
215 1 1 1
|
|
230 1 1 1
|
|
380 1 1 1
|
|
500 1 1 1
|
|
900 1 1 1
|
|
</tableData>
|
|
</table>
|
|
|
|
<property>fcs/pitch-cmd-summer</property>
|
|
<value>-0.5</value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<tableData>
|
|
19 25 35
|
|
90 38.8840 25.9906 25.9906
|
|
180 38.8840 25.9906 25.9906
|
|
200 38.8840 25.9906 25.9906
|
|
215 58.8840 25.9906 25.9906
|
|
230 81.9605 58.8840 25.9906
|
|
380 63.4645 56.8517 34.4889
|
|
500 61.1371 58.5955 33.0386
|
|
900 48.8597 42.1147 42.1147
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
<product>
|
|
<property>fcs/w-velocity-norm</property>
|
|
<value>0</value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<tableData>
|
|
19 25 35
|
|
90 -0.0231 -0.0119 -0.0119
|
|
180 -0.0231 -0.0119 -0.0119
|
|
200 -0.0231 -0.0119 -0.0119
|
|
215 -0.0231 -0.0119 -0.0119
|
|
230 -0.0406 -0.0231 -0.0119
|
|
380 -0.0244 -0.0195 -0.0159
|
|
500 -0.0115 -0.0085 -0.0061
|
|
900 -0.0045 -0.0029 -0.0029
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
<product>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<tableData>
|
|
19 25 35
|
|
90 1 1 1
|
|
180 1 1 1
|
|
200 1 1 1
|
|
215 1 1 1
|
|
230 1 1 1
|
|
380 1 1 1
|
|
500 1 1 1
|
|
900 1 1 1
|
|
</tableData>
|
|
</table>
|
|
<property>velocities/q-aero-rad_sec</property>
|
|
<value>-0.3</value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<tableData>
|
|
19 25 35
|
|
90 -34.0297 -19.6316 -19.6316
|
|
180 -34.0297 -19.6316 -19.6316
|
|
200 -34.0297 -19.6316 -19.6316
|
|
215 -44.0297 -19.6316 -19.6316
|
|
230 -62.1151 -44.0297 -19.6316
|
|
380 -47.3350 -42.1836 -26.0436
|
|
500 -45.4195 -43.0593 -24.6616
|
|
900 -35.7627 -30.5733 -30.5733
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</sum>
|
|
</function>
|
|
<clipto>
|
|
<min>-5</min>
|
|
<max>5</max>
|
|
</clipto>
|
|
</fcs_function>
|
|
|
|
<aerosurface_scale name="fcs/el-reg-scale">
|
|
<input> fcs/el-pitch-cmd </input>
|
|
<domain>
|
|
<min> -5 </min>
|
|
<max> 5 </max>
|
|
</domain>
|
|
<range>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</range>
|
|
</aerosurface_scale >
|
|
|
|
<actuator name="fcs/elevator-act">
|
|
<input> fcs/el-reg-scale</input>
|
|
<lag> 0.0 </lag>
|
|
<rate_limit> 2 </rate_limit>
|
|
<clipto>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</clipto>
|
|
<output>fcs/elevator-pos-norm</output>
|
|
</actuator>
|
|
|
|
<aerosurface_scale name="fcs/elevator-position">
|
|
<input>fcs/elevator-pos-norm</input>
|
|
<range>
|
|
<min>-0.5236</min>
|
|
<max>0.5236</max>
|
|
</range>
|
|
<output>fcs/elevator-pos-rad</output>
|
|
</aerosurface_scale>
|
|
|
|
<summer name="fcs/dht-left-pos-rad">
|
|
<input>-fcs/elevator-pos-rad</input>
|
|
<input>-fcs/left-aileron-pos-rad</input>
|
|
<clipto>
|
|
<min>-0.5236</min>
|
|
<max>0.5236</max>
|
|
</clipto>
|
|
</summer>
|
|
|
|
<summer name="fcs/dht-right-pos-rad">
|
|
<input>fcs/elevator-pos-rad</input>
|
|
<input>fcs/right-aileron-pos-rad</input>
|
|
<clipto>
|
|
<min>-0.5236</min>
|
|
<max>0.5236</max>
|
|
</clipto>
|
|
</summer>
|
|
|
|
<!-- Reduce TVC gains if AB is on-->
|
|
<switch name="fcs/tvc-gain-select">
|
|
<default value="1"/>
|
|
<test logic="AND" value="0.6">
|
|
fcs/throttle-pos-norm ge 0.99
|
|
</test>
|
|
</switch>
|
|
|
|
<!-- LQR Tracker Integral TVC pitch rate controller-->
|
|
<fcs_function name="fcs/tvc-pitch-cmd">
|
|
<!-- description>thrust vector control lqr regulator</description -->
|
|
<function>
|
|
<product>
|
|
<sum>
|
|
<product>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<tableData>
|
|
12 20 30 60
|
|
70 0.4 0.4 0.3 0.3
|
|
140 0.4 0.4 0.3 0.3
|
|
200 0.4 0.45 0.35 0.3
|
|
215 0.4 0.45 0.35 0.3
|
|
230 0.4 0.45 0.35 0.3
|
|
330 0.4 0.45 0.35 0.3
|
|
380 0.4 0.4 0.4 0.4
|
|
500 0.4 0.4 0.4 0.4
|
|
900 0.4 0.4 0.4 0.4
|
|
</tableData>
|
|
</table>
|
|
<property>fcs/pitch-cmd-summer</property>
|
|
<value>-1</value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<independentVar lookup="table">position/h-sl-ft</independentVar>
|
|
<tableData breakPoint="-1000">
|
|
12 20 30
|
|
70 97.6705 95.6705 95.6705
|
|
140 97.6705 95.6705 95.6705
|
|
200 97.6705 95.6705 95.6705
|
|
215 67.9777 95.6705 95.6705
|
|
230 0 67.9777 95.6705
|
|
330 0 0 0
|
|
380 0 0 0
|
|
500 0 0 0
|
|
900 0 0 0
|
|
</tableData>
|
|
<tableData breakPoint="30000">
|
|
12 20 30
|
|
70 97.6705 95.6705 95.6705
|
|
140 97.6705 95.6705 95.6705
|
|
200 97.6705 95.6705 95.6705
|
|
215 67.9777 95.6705 95.6705
|
|
230 0 67.9777 95.6705
|
|
330 0 49.6594 70.1697
|
|
380 0 34.2680 34.2680
|
|
500 0 0 0
|
|
900 0 0 0
|
|
</tableData>
|
|
<tableData breakPoint="70000">
|
|
12 20 30
|
|
70 97.6705 95.6705 95.6705
|
|
140 97.6705 95.6705 95.6705
|
|
200 97.6705 95.6705 95.6705
|
|
215 67.9777 95.6705 95.6705
|
|
230 0 67.9777 95.6705
|
|
330 0 56.0773 75.1918
|
|
380 0 56.0773 75.1918
|
|
500 0 49.6594 70.1697
|
|
900 0 34.2680 34.2680
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
<product>
|
|
<property>fcs/w-velocity-norm</property>
|
|
<value>-0</value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<independentVar lookup="table">position/h-sl-ft</independentVar>
|
|
<tableData breakPoint="-1000">
|
|
12 20 30
|
|
70 -0.0444 -0.0444 -0.0444
|
|
140 -0.0444 -0.0444 -0.0444
|
|
200 -0.0444 -0.0444 -0.0444
|
|
215 -0.0271 -0.0444 -0.0444
|
|
230 0 -0.0271 -0.0444
|
|
330 0 0 0
|
|
380 0 0 0
|
|
500 0 0 0
|
|
900 0 0 0
|
|
</tableData>
|
|
<tableData breakPoint="30000">
|
|
12 20 30
|
|
70 -0.0444 -0.0444 -0.0444
|
|
140 -0.0444 -0.0444 -0.0444
|
|
200 -0.0444 -0.0444 -0.0444
|
|
215 -0.0271 -0.0444 -0.0444
|
|
230 0 -0.0271 -0.0444
|
|
330 0 -0.0073 -0.0130
|
|
380 0 -0.0024 -0.0024
|
|
500 0 0 0
|
|
900 0 0 0
|
|
</tableData>
|
|
<tableData breakPoint="70000">
|
|
12 20 30
|
|
70 -0.0444 -0.0444 -0.0444
|
|
140 -0.0444 -0.0444 -0.0444
|
|
200 -0.0444 -0.0444 -0.0444
|
|
215 -0.0271 -0.0444 -0.0444
|
|
230 0 -0.0271 -0.0444
|
|
330 0 -0.0195 -0.0349
|
|
380 0 -0.0195 -0.0349
|
|
500 0 -0.0073 -0.0130
|
|
900 0 -0.0024 -0.0024
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
<product>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<tableData>
|
|
12 20 30
|
|
70 0.2 0.2 0.2
|
|
140 0.2 0.2 0.2
|
|
200 0.2 0.2 0.2
|
|
215 0.2 0.2 0.2
|
|
230 0.225 0.2 0.2
|
|
330 0.225 0.225 0.2
|
|
380 0.225 0.225 0.2
|
|
500 0.225 0.225 0.2
|
|
900 0.225 0.225 0.2
|
|
</tableData>
|
|
</table>
|
|
<property>velocities/q-aero-rad_sec</property>
|
|
<value>-1</value>
|
|
<table>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<independentVar lookup="table">position/h-sl-ft</independentVar>
|
|
<tableData breakPoint="-1000">
|
|
12 20 30
|
|
70 -72.1205 -72.1205 -72.1205
|
|
140 -72.1205 -72.1205 -72.1205
|
|
200 -72.1205 -72.1205 -72.1205
|
|
215 -50.7416 -72.1205 -72.1205
|
|
230 0 -50.7416 -72.1205
|
|
330 0 0 0
|
|
380 0 0 0
|
|
500 0 0 0
|
|
900 0 0 0
|
|
</tableData>
|
|
<tableData breakPoint="30000">
|
|
12 20 30
|
|
70 -72.1205 -72.1205 -72.1205
|
|
140 -72.1205 -72.1205 -72.1205
|
|
200 -72.1205 -72.1205 -72.1205
|
|
215 -50.7416 -72.1205 -72.1205
|
|
230 0 -50.7416 -72.1205
|
|
330 0 -36.1358 -51.7437
|
|
380 0 -24.8715 -24.8715
|
|
500 0 0 0
|
|
900 0 0 0
|
|
</tableData>
|
|
<tableData breakPoint="70000">
|
|
12 20 30
|
|
70 -72.1205 -72.1205 -72.1205
|
|
140 -72.1205 -72.1205 -72.1205
|
|
200 -72.1205 -72.1205 -72.1205
|
|
215 -50.7416 -72.1205 -72.1205
|
|
230 0 -50.7416 -72.1205
|
|
330 0 -41.5043 -56.5934
|
|
380 0 -41.5043 -56.5934
|
|
500 0 -36.1358 -51.7437
|
|
900 0 -24.8715 -24.8715
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</sum>
|
|
<value>1</value>
|
|
</product>
|
|
</function>
|
|
<clipto>
|
|
<min>-5</min>
|
|
<max>5</max>
|
|
</clipto>
|
|
</fcs_function>
|
|
|
|
<!-- inhibit the tvc if gear down -->
|
|
<pure_gain name="fcs/tvc-gain">
|
|
<input>fcs/tvc-pitch-cmd</input>
|
|
<gain>fcs/tvc-inhibit</gain>
|
|
</pure_gain>
|
|
|
|
<!-- reduce tvc gain for burner on -->
|
|
<pure_gain name="fcs/tvc-gain-hi-lo">
|
|
<input>fcs/tvc-gain</input>
|
|
<gain>1</gain>
|
|
</pure_gain>
|
|
|
|
<!--TVC used for trim in high altitude supersonic flight-->
|
|
<!-- Uses TVC to reduce trim setting of elevator for reduced drag-->
|
|
<fcs_function name="fcs/ss-trim">
|
|
<function>
|
|
<product>
|
|
<sum>
|
|
<product>
|
|
<value>7.0626</value>
|
|
<property>fcs/pitch-rate-integrator</property>
|
|
</product>
|
|
<product>
|
|
<value>-0.0019</value>
|
|
<property>fcs/u-velocity-norm</property>
|
|
</product>
|
|
<product>
|
|
<value>0.0083</value>
|
|
<property>fcs/w-velocity-norm</property>
|
|
</product>
|
|
<product>
|
|
<value>-5.1005</value>
|
|
<property>velocities/q-aero-rad_sec</property>
|
|
</product>
|
|
</sum>
|
|
<table>
|
|
<independentVar lookup="row">velocities/mach</independentVar>
|
|
<independentVar lookup="column">position/h-sl-ft</independentVar>
|
|
<tableData>
|
|
45000 50000
|
|
0.92 0 0
|
|
0.95 0 1.5
|
|
1.00 0 2.5
|
|
1.10 0 3.5
|
|
1.15 0 4
|
|
1.20 0 2.5
|
|
1.25 0 2
|
|
1.30 0 1.5
|
|
1.35 0 1.5
|
|
1.40 0 1
|
|
1.45 0 0.9
|
|
1.50 0 0.75
|
|
1.55 0 0.7
|
|
1.60 0 0.65
|
|
1.7 0 0.6
|
|
1.8 0 0.6
|
|
1.9 0 0.6
|
|
2.0 0 0.6
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<clipto>
|
|
<min>-0.7</min>
|
|
<max>0.05</max>
|
|
</clipto>
|
|
</fcs_function>
|
|
|
|
<!-- In situations where TVC control is not called for, disable TVC SS Trim if manuevering-->
|
|
<fcs_function name="fcs/ss-trim-override">
|
|
<function>
|
|
<table>
|
|
<independentVar lookup="row">velocities/q-aero-rad_sec</independentVar>
|
|
<tableData>
|
|
-0.15 0
|
|
-0.1 1
|
|
0.0 1
|
|
0.1 1
|
|
0.15 0
|
|
</tableData>
|
|
</table>
|
|
</function>
|
|
</fcs_function>
|
|
|
|
<!-- inhibit the ss trim if manuevering-->
|
|
<pure_gain name="fcs/ss-trim-gain">
|
|
<input>fcs/ss-trim</input>
|
|
<gain>fcs/ss-trim-override</gain>
|
|
</pure_gain>
|
|
|
|
<summer name="fcs/tvc-summer">
|
|
<input>fcs/tvc-gain-hi-lo</input>
|
|
<input>fcs/ss-trim-gain</input>
|
|
</summer>
|
|
|
|
<aerosurface_scale name="fcs/tvc-reg-scale">
|
|
<input> fcs/tvc-summer</input>
|
|
<domain>
|
|
<min> -5 </min>
|
|
<max> 5 </max>
|
|
</domain>
|
|
<range>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</range>
|
|
</aerosurface_scale >
|
|
|
|
<pure_gain name="fcs/tvc-act">
|
|
<input> fcs/tvc-cmd-norm</input>
|
|
<gain>1</gain>
|
|
<clipto>
|
|
<min> -1 </min>
|
|
<max> 1 </max>
|
|
</clipto>
|
|
<output>fcs/tvc-pos-norm</output>
|
|
</pure_gain>
|
|
|
|
<aerosurface_scale name="fcs/tvc-position">
|
|
<input>fcs/tvc-pos-norm</input>
|
|
<range>
|
|
<min>-0.349</min>
|
|
<max>0.349</max>
|
|
</range>
|
|
<output>fcs/tvc-pos-rad</output>
|
|
</aerosurface_scale>
|
|
|
|
</channel>
|
|
|
|
<channel name="Leading Edge Flap">
|
|
|
|
<pure_gain name="fcs/lef-alpha-gain">
|
|
<input>aero/alpha-deg</input>
|
|
<gain>1.38</gain>
|
|
</pure_gain>
|
|
|
|
<lead_lag_filter name="fcs/lef-alpha-filter">
|
|
<input>fcs/lef-alpha-gain</input>
|
|
<c1> 2 </c1>
|
|
<c2> 7.25 </c2>
|
|
<c3> 1 </c3>
|
|
<c4> 7.25 </c4>
|
|
</lead_lag_filter>
|
|
|
|
<fcs_function name="fcs/lef-transfer-function">
|
|
<function>
|
|
<description>leading edge flap control function</description>
|
|
<sum>
|
|
<property> fcs/lef-alpha-filter </property>
|
|
<product>
|
|
<quotient>
|
|
<property>aero/qbar-psf</property>
|
|
<property>atmosphere/P-psf</property>
|
|
</quotient>
|
|
<value>-9.05</value>
|
|
</product>
|
|
<value>1.45</value>
|
|
</sum>
|
|
</function>
|
|
</fcs_function>
|
|
|
|
<pure_gain name="fcs/lef-deg-to-rad">
|
|
<input>fcs/lef-transfer-function</input>
|
|
<gain>0.01745</gain>
|
|
<clipto>
|
|
<min> -0.001 </min>
|
|
<max> 0.6108 </max>
|
|
</clipto>
|
|
</pure_gain>
|
|
|
|
<switch name="fcs/lef-pos">
|
|
<default value="0.0"/>
|
|
<test logic="AND" value="0">
|
|
gear/wow eq 1
|
|
gear/gear-pos-norm gt 0
|
|
</test>
|
|
<test value="fcs/lef-deg-to-rad">
|
|
gear/gear-pos-norm == 0
|
|
</test>
|
|
<test logic="AND" value="0">
|
|
velocities/mach gt 0.9
|
|
</test>
|
|
</switch>
|
|
|
|
<pure_gain name="fcs/lef-norm">
|
|
<input>fcs/lef-pos</input>
|
|
<gain>1.637197</gain>
|
|
</pure_gain>
|
|
|
|
<kinematic name="fcs/lef-control">
|
|
<input>fcs/lef-norm</input>
|
|
<traverse>
|
|
<setting>
|
|
<position>-1.0</position>
|
|
<time>0.55</time>
|
|
</setting>
|
|
<setting>
|
|
<position>1.0</position>
|
|
<time>0.55</time>
|
|
</setting>
|
|
</traverse>
|
|
<output>fcs/lef-pos-norm</output>
|
|
</kinematic>
|
|
|
|
<aerosurface_scale name="fcs/lef-deg">
|
|
<input>fcs/lef-control</input>
|
|
<domain>
|
|
<min>-1.0</min>
|
|
<max>1.0</max>
|
|
</domain>
|
|
<range>
|
|
<min>0</min>
|
|
<max>35</max>
|
|
</range>
|
|
<output>fcs/lef-pos-deg</output>
|
|
</aerosurface_scale>
|
|
|
|
<aerosurface_scale name="fcs/lef-pos-rad">
|
|
<input>fcs/lef-control</input>
|
|
<domain>
|
|
<min>-1.0</min>
|
|
<max>1.0</max>
|
|
</domain>
|
|
<range>
|
|
<min>0</min>
|
|
<max>0.6108</max>
|
|
</range>
|
|
<output>fcs/lef-pos-rad</output>
|
|
</aerosurface_scale>
|
|
|
|
</channel>
|
|
|
|
<channel name="Throttle">
|
|
|
|
<!--FADEC function to automatically add throttle in post stall conditions for TVC pitch authority-->
|
|
<fcs_function name="fcs/throttle-adjust">
|
|
<function>
|
|
<table>
|
|
<independentVar lookup="column">aero/alpha-deg</independentVar>
|
|
<independentVar lookup="row">velocities/vc-kts</independentVar>
|
|
<tableData>
|
|
0 20 30 40 50
|
|
0 0.85 0.9 0.98 1 1
|
|
50 0.8 0.85 0.95 1 1
|
|
60 0.75 0.65 0.93 1 1
|
|
70 0.7 0.55 0.9 0.98 1
|
|
80 0.65 0.5 0.85 0.98 1
|
|
90 0.6 0.7 0.8 0.95 1
|
|
100 0.55 0.65 0.75 0.85 1
|
|
110 0.4 0.5 0.6 0.65 1
|
|
120 0.2 0.3 0.35 0.35 1
|
|
130 0.1 0.2 0.25 0.25 0.5
|
|
1000 0.1 0.1 0.2 0.25 0.5
|
|
</tableData>
|
|
</table>
|
|
</function>
|
|
</fcs_function>
|
|
|
|
<pure_gain name="fcs/throttle-gain">
|
|
<input>fcs/throttle-adjust</input>
|
|
<gain>fcs/tvc-inhibit</gain>
|
|
<output>fcs/throttle-override</output>
|
|
</pure_gain>
|
|
|
|
<!-- Throttle filter -->
|
|
<lag_filter name="fcs/throttle-filter">
|
|
<input>fcs/throttle-cmd-norm</input>
|
|
<c1>1</c1>
|
|
</lag_filter>
|
|
|
|
<summer name="fcs/t1-summer">
|
|
<input>fcs/throttle-filter</input>
|
|
<!--input>fcs/throttle-override</input-->
|
|
<clipto>
|
|
<min>fcs/throttle-override</min>
|
|
<max>1</max>
|
|
</clipto>
|
|
</summer>
|
|
|
|
<pure_gain name="fcs/throttle1">
|
|
<input>fcs/t1-summer</input>
|
|
<gain>1.001</gain>
|
|
<output>fcs/throttle-pos-norm</output>
|
|
</pure_gain>
|
|
|
|
<!-- Throttle filter -->
|
|
<lag_filter name="fcs/throttle1-filter">
|
|
<input>fcs/throttle-cmd-norm[1]</input>
|
|
<c1>1</c1>
|
|
</lag_filter>
|
|
|
|
<summer name="fcs/t2-summer">
|
|
<input>fcs/throttle1-filter</input>
|
|
<!--input>fcs/throttle-override</input-->
|
|
<clipto>
|
|
<min>fcs/throttle-override</min>
|
|
<max>1</max>
|
|
</clipto>
|
|
</summer>
|
|
|
|
<pure_gain name="fcs/throttle2">
|
|
<input>fcs/t2-summer</input>
|
|
<gain>1.001</gain>
|
|
<output>fcs/throttle-pos-norm[1]</output>
|
|
</pure_gain>
|
|
|
|
<!-- Needed to compute TVC pitch moment contribution-->
|
|
<fcs_function name="fcs/thrust-normalized">
|
|
<!-- description>Normalized thrust output</description -->
|
|
<function>
|
|
<quotient>
|
|
<property>propulsion/engine/thrust-lbs</property>
|
|
<value>26550</value>
|
|
</quotient>
|
|
</function>
|
|
<clipto>
|
|
<min> 0 </min>
|
|
<max> 1.5 </max>
|
|
</clipto>
|
|
<output>fcs/thrust-norm</output>
|
|
</fcs_function>
|
|
|
|
</channel>
|
|
|
|
<channel name="Flaps">
|
|
|
|
<switch name="fcs/tef-pos">
|
|
<default value="0.0"/>
|
|
<test logic="AND" value="1">
|
|
velocities/vc-kts lt 180
|
|
velocities/mach lt 0.4
|
|
</test>
|
|
<test logic="AND" value="0.5235">
|
|
velocities/vc-kts lt 200
|
|
velocities/mach lt 0.45
|
|
</test>
|
|
<test logic="AND" value="0.26175">
|
|
velocities/vc-kts lt 225
|
|
velocities/mach lt 0.5
|
|
</test>
|
|
<test logic="AND" value="0.13">
|
|
velocities/vc-kts lt 240
|
|
velocities/mach lt 0.55
|
|
</test>
|
|
<test logic="AND" value="0.065">
|
|
velocities/vc-kts lt 255
|
|
velocities/mach lt 0.6
|
|
</test>
|
|
</switch>
|
|
|
|
<pure_gain name="fcs/tef-norm">
|
|
<input>fcs/tef-pos</input>
|
|
<gain>1.91</gain>
|
|
</pure_gain>
|
|
|
|
<kinematic name="fcs/flap-controller">
|
|
<input>fcs/tef-norm</input>
|
|
<traverse>
|
|
<setting>
|
|
<position>0</position>
|
|
<time>0</time>
|
|
</setting>
|
|
<setting>
|
|
<position>0.5</position>
|
|
<time>3.0</time>
|
|
</setting>
|
|
<setting>
|
|
<position>1.0</position>
|
|
<time>3.0</time>
|
|
</setting>
|
|
</traverse>
|
|
<output>fcs/flap-pos-norm</output>
|
|
</kinematic>
|
|
|
|
<summer name="fcs/flap-pos-out">
|
|
<input>fcs/flap-controller</input>
|
|
<input>fcs/speedbrake-flap</input>
|
|
<clipto>
|
|
<min> 0 </min>
|
|
<max> 1 </max>
|
|
</clipto>
|
|
</summer>
|
|
|
|
<aerosurface_scale name="fcs/tef-pos-deg">
|
|
<input>fcs/flap-pos-out</input>
|
|
<domain>
|
|
<min>0</min>
|
|
<max>1.0</max>
|
|
</domain>
|
|
<range>
|
|
<min>0</min>
|
|
<max>30</max>
|
|
</range>
|
|
<output>fcs/flap-pos-deg</output>
|
|
</aerosurface_scale>
|
|
|
|
</channel>
|
|
|
|
<!-- Speedbrake currently borrowed from F-16 -->
|
|
<channel name="Speedbrake">
|
|
<!--
|
|
- To prevent deep stall the Flight Computer commands speedbrake
|
|
- deflection at high angle of attack (alpha) and low speeds. This
|
|
- will provide just enough pitch down moment to keep the aircraft
|
|
- under control.
|
|
-->
|
|
<switch name="fcs/speedbrake-alpha-limiter">
|
|
<default value="0"/>
|
|
<test logic="AND" value="1">
|
|
aero/alpha-deg ge 120
|
|
velocities/v-fps le 10
|
|
</test>
|
|
</switch>
|
|
|
|
<switch name="fcs/speedbrake-initiate">
|
|
<default value="0"/>
|
|
<test logic="OR" value="1">
|
|
fcs/speedbrake-alpha-limiter eq 1
|
|
fcs/speedbrake-cmd-norm eq 1
|
|
</test>
|
|
</switch>
|
|
|
|
<kinematic name="fcs/speedbrake-control">
|
|
<input>fcs/speedbrake-initiate</input>
|
|
<traverse>
|
|
<setting>
|
|
<position>0</position>
|
|
<time>0</time>
|
|
</setting>
|
|
<setting>
|
|
<position>60</position>
|
|
<time>1</time>
|
|
</setting>
|
|
</traverse>
|
|
<output>fcs/speedbrake-pos-deg</output>
|
|
</kinematic>
|
|
|
|
<aerosurface_scale name="fcs/speedbrake-position-normalizer">
|
|
<input>fcs/speedbrake-control</input>
|
|
<domain>
|
|
<min>0</min>
|
|
<max>60</max>
|
|
</domain>
|
|
<range>
|
|
<min>0</min>
|
|
<max>1</max>
|
|
</range>
|
|
<output>fcs/speedbrake-pos-norm</output>
|
|
</aerosurface_scale>
|
|
|
|
<!-- F-22 uses flaps, ailerons and rudders for speedbrakes. Outputs are
|
|
used to animate surfaces during speedbrake deployment-->
|
|
<pure_gain name="fcs/speedbrake-aileron">
|
|
<input>fcs/speedbrake-pos-norm</input>
|
|
<gain>-1</gain>
|
|
<output>fcs/speedbrake-aileron</output>
|
|
</pure_gain>
|
|
|
|
<pure_gain name="fcs/speedbrake-ail-right">
|
|
<input>fcs/speedbrake-pos-norm</input>
|
|
<gain>-1</gain>
|
|
<output>fcs/speedbrake-aileron-right</output>
|
|
</pure_gain>
|
|
|
|
<pure_gain name="fcs/speedbrake-rudder">
|
|
<input>fcs/speedbrake-pos-norm</input>
|
|
<gain>1</gain>
|
|
<output>fcs/speedbrake-rudder</output>
|
|
</pure_gain>
|
|
|
|
<pure_gain name="fcs/speedbrake-flaps">
|
|
<input>fcs/speedbrake-pos-norm</input>
|
|
<gain>1</gain>
|
|
<output>fcs/speedbrake-flap</output>
|
|
</pure_gain>
|
|
|
|
</channel>
|
|
|
|
<channel name="Landing Gear">
|
|
|
|
<kinematic name="fcs/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>
|
|
|
|
<scheduled_gain name="fcs/scheduled-steer-pos-deg">
|
|
<input>fcs/steer-cmd-norm</input>
|
|
<table>
|
|
<independentVar>velocities/vg-fps</independentVar>
|
|
<tableData>
|
|
10.0 80
|
|
50.0 15
|
|
150.0 2
|
|
</tableData>
|
|
</table>
|
|
<output>fcs/steer-pos-deg</output>
|
|
</scheduled_gain>
|
|
|
|
</channel>
|
|
|
|
</flight_control>
|
|
|
|
<aerodynamics>
|
|
|
|
<!-- Shift the aero ref point aft. F-22 is 10% unstable at subsonic, stable at around Mach 1.2+ -->
|
|
<function name="aero_ref_pt_shift_x">
|
|
<table>
|
|
<independentVar>velocities/mach</independentVar>
|
|
<tableData>
|
|
0.0000 0.0000
|
|
0.6000 0.01
|
|
0.8000 0.025
|
|
0.9000 0.035
|
|
1.0000 0.045
|
|
1.1000 0.1
|
|
1.2000 0.105
|
|
1.3000 0.11
|
|
</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 1.3893
|
|
0.1000 1.2108
|
|
0.1500 1.1972
|
|
0.2000 1.2108
|
|
0.3000 1.1785
|
|
0.4000 1.0697
|
|
0.5000 1.0578
|
|
0.6000 1.0323
|
|
0.7000 1.0136
|
|
0.8000 1.0051
|
|
0.9000 1.0017
|
|
1.0000 1.0000
|
|
1.1000 1.0000
|
|
</tableData>
|
|
</table>
|
|
</function>
|
|
|
|
<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 0.5235
|
|
0.1000 0.4759
|
|
0.1500 0.5250
|
|
0.2000 0.5388
|
|
0.3000 0.5924
|
|
0.4000 0.6471
|
|
0.5000 0.6941
|
|
0.6000 0.7624
|
|
0.7000 0.8253
|
|
0.8000 0.8812
|
|
0.9000 0.9412
|
|
1.0000 1.0000
|
|
1.1000 1.0000
|
|
</tableData>
|
|
</table>
|
|
</function>
|
|
|
|
<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>
|
|
<property>aero/function/kCDge</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-1.5700 1.5000
|
|
-0.2600 0.0480
|
|
0.0000 0.00820
|
|
0.2600 0.0480
|
|
1.5700 1.5000
|
|
</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>
|
|
<property>aero/function/kCDge</property>
|
|
<value>0.0700</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>velocities/mach</independentVar>
|
|
<tableData>
|
|
0.0000 0.0000
|
|
0.8100 0.0000
|
|
1.1000 0.0220
|
|
1.8000 0.0140
|
|
2.4000 0.020
|
|
</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>
|
|
<property>aero/function/kCDge</property>
|
|
<value>0.0750</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>0.0200</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>0.0240</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/function/kCDge</property>
|
|
<table>
|
|
<independentVar>aero/beta-rad</independentVar>
|
|
<tableData>
|
|
-1.5700 1.2300
|
|
-0.2600 0.0500
|
|
0.0000 0.0000
|
|
0.2600 0.0500
|
|
1.5700 1.2300
|
|
</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>aero/function/kCDge</property>
|
|
<table>
|
|
<independentVar>fcs/elevator-pos-rad</independentVar>
|
|
<tableData>
|
|
-0.5236 0.075
|
|
-0.218 0.0375
|
|
0 0.010
|
|
0.218 0.0375
|
|
0.5236 0.077
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/coefficient/CDDlef">
|
|
<description>Drag_due_to_leading_edge_flap_deflection</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>aero/function/kCDge</property>
|
|
<property>fcs/lef-pos-rad</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.175 0.003
|
|
-0.087 0.001
|
|
0.000 0.000
|
|
0.087 0.001
|
|
0.175 0.002
|
|
0.262 0.004
|
|
0.349 0.007
|
|
0.436 0.011
|
|
0.524 0.015
|
|
0.611 0.019
|
|
0.698 0.023
|
|
0.785 0.024
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CDq">
|
|
<description>Drag_due_to_pitch_rate</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>velocities/q-aero-rad_sec</property>
|
|
<property>aero/ci2vel</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.175 -1.265
|
|
-0.087 -2.139
|
|
0.000 -0.308
|
|
0.087 1.402
|
|
0.175 3.369
|
|
0.262 5.135
|
|
0.349 6.880
|
|
0.436 8.060
|
|
0.524 11.201
|
|
0.611 13.872
|
|
0.698 19.217
|
|
0.785 22.105
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CDq_Dlef">
|
|
<description>Drag_due_to_pitch_rate_and_leading_edge_flap_deflection</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>velocities/q-aero-rad_sec</property>
|
|
<property>aero/ci2vel</property>
|
|
<property>fcs/lef-pos-rad</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.175 0.067
|
|
-0.087 0.034
|
|
0.000 0.028
|
|
0.087 0.029
|
|
0.175 0.033
|
|
0.262 0.059
|
|
0.349 0.061
|
|
0.436 0.027
|
|
0.524 0.036
|
|
0.611 0.047
|
|
0.698 0.029
|
|
0.785 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>
|
|
<property>aero/beta-rad</property>
|
|
<value>-1.7875</value>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CYb_M">
|
|
<description>Side_force_due_to_beta_due_to_mach</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>aero/beta-rad</property>
|
|
<table>
|
|
<independentVar>velocities/mach</independentVar>
|
|
<tableData>
|
|
0.4 0.0
|
|
1.2 0.0573
|
|
1.6 -0.1719
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CYbdot">
|
|
<description>Side_force_due_to_beta_rate</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>aero/betadot-rad_sec</property>
|
|
<value>-0.0458</value>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CYDa">
|
|
<description>Side_force_due_to_aileron</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>fcs/left-aileron-pos-rad</property>
|
|
<value>-1.1516e-3</value>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CYDr">
|
|
<description>Side_force_due_to_rudder</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>fcs/rudder-pos-rad</property>
|
|
<value>0.0619</value>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CYp">
|
|
<description>Side_force_due_to_roll_rate</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>aero/bi2vel</property>
|
|
<property>velocities/p-aero-rad_sec</property>
|
|
<value>0.0399</value>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CYr">
|
|
<description>Side_force_due_to_yaw_rate</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>aero/bi2vel</property>
|
|
<property>velocities/r-aero-rad_sec</property>
|
|
<value>0.1218</value>
|
|
</product>
|
|
</function>
|
|
</axis>
|
|
|
|
<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>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.1745 -0.4279
|
|
0.7854 2.3000
|
|
1.3963 1.0726
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/coefficient/CLDlef">
|
|
<description>Lift_due_to_leading_edge_flap_deflection</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>fcs/lef-pos-rad</property>
|
|
<property>aero/function/kCLge</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.1750 -0.0120
|
|
-0.0870 -0.0040
|
|
0.0000 0.0020
|
|
0.0870 0.0070
|
|
0.1750 0.0120
|
|
0.2620 0.0180
|
|
0.3490 0.0220
|
|
0.4360 0.0250
|
|
0.5240 0.0260
|
|
0.6110 0.0280
|
|
0.6980 0.0300
|
|
0.7850 0.032
|
|
0.8727 0.03
|
|
1.0472 0.028
|
|
1.2217 0.025
|
|
1.3963 0.02
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CLadot">
|
|
<description>Lift_due_to_alpha_rate</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>aero/alphadot-rad_sec</property>
|
|
<property>aero/ci2vel</property>
|
|
<value>2.5602</value>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CLq">
|
|
<description>Lift_due_to_pitch_rate</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>velocities/q-aero-rad_sec</property>
|
|
<property>aero/ci2vel</property>
|
|
<property>aero/function/kCLge</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.175 8.7127
|
|
-0.087 25.7114
|
|
0.000 28.9000
|
|
0.087 31.3973
|
|
0.175 31.0872
|
|
0.262 30.4071
|
|
0.349 28.9735
|
|
0.436 28.4242
|
|
0.524 27.8647
|
|
0.611 27.2654
|
|
0.698 30.5158
|
|
0.785 27.8165
|
|
</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>
|
|
<property>aero/function/kCLge</property>
|
|
<value>0.3500</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>
|
|
<property>aero/function/kCLge</property>
|
|
<value>0.3500</value>
|
|
</product>
|
|
</function>
|
|
<!--
|
|
<function name="aero/coefficient/CLDh">
|
|
<description>Lift_due_to_horizontal_tail_deflection</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/elevator-pos-rad</independentVar>
|
|
<tableData>
|
|
-0.1745 -0.4279
|
|
0.0000 0.1346
|
|
0.7854 2.00
|
|
1.3963 1.0726
|
|
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/coefficient/CLDh">
|
|
<description>Lift_due_to_horizontal_tail_deflection</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/elevator-pos-rad</independentVar>
|
|
<tableData>
|
|
|
|
-0.175 -0.428
|
|
-0.087 -0.135
|
|
0.000 0.135
|
|
0.087 0.414
|
|
0.175 0.725
|
|
0.262 1.041
|
|
0.349 1.327
|
|
0.436 1.547
|
|
0.524 1.737
|
|
0.611 1.829
|
|
0.698 1.930
|
|
0.785 2.000
|
|
0.8727 1.982
|
|
1.0472 1.830
|
|
1.2217 1.548
|
|
1.3963 1.073
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
-->
|
|
<function name="aero/coefficient/CLde">
|
|
<description>Lift_due_to_elevator</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>fcs/elevator-pos-rad</property>
|
|
<property>aero/function/kCLge</property>
|
|
<value>0.190</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>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.0873 0.0189
|
|
0.0000 0.0176
|
|
0.0873 0.0119
|
|
0.1745 0.0050
|
|
0.2618 0.0049
|
|
0.3491 0.0028
|
|
0.4363 0.0084
|
|
0.5236 0.0171
|
|
0.6109 0.0044
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Clda_M">
|
|
<description>Change_in_Roll_moment_due_to_aileron_due_to_mach</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>aero/alpha-rad</property>
|
|
<property>fcs/left-aileron-pos-rad</property>
|
|
<table>
|
|
<independentVar>velocities/mach</independentVar>
|
|
<tableData>
|
|
0.6 0.0
|
|
1.2 -0.063
|
|
1.6 -0.063
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Cldr_M">
|
|
<description>Change_in_Roll_moment_due_to_rudder_due_to_mach</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>aero/alpha-rad</property>
|
|
<property>fcs/rudder-pos-rad</property>
|
|
<table>
|
|
<independentVar>velocities/mach</independentVar>
|
|
<tableData>
|
|
0.6 0.0
|
|
1.6 -0.0201
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Clbdot">
|
|
<description>Roll_moment_due_to_beta_rate</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>aero/bi2vel</property>
|
|
<property>aero/betadot-rad_sec</property>
|
|
<value>-0.0037</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>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
0.0000 -0.4000
|
|
0.3490 -0.3100
|
|
</tableData>
|
|
</table>
|
|
</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>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.175 -0.126
|
|
-0.087 -0.026
|
|
0.0 0.063
|
|
0.087 0.113
|
|
0.175 0.208
|
|
0.262 0.230
|
|
0.349 0.319
|
|
0.436 0.437
|
|
0.524 0.680
|
|
0.611 0.100
|
|
0.698 0.447
|
|
0.785 -0.330
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Clda">
|
|
<description>Roll_moment_due_to_aileron</description>
|
|
<product>
|
|
<value>4</value>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>fcs/left-aileron-pos-rad</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.1745 0.045
|
|
-0.0873 0.052
|
|
0.0000 0.060
|
|
0.0873 0.057
|
|
0.1745 0.052
|
|
0.2618 0.047
|
|
0.3491 0.040
|
|
0.4363 0.034
|
|
0.5236 0.029
|
|
0.6109 0.023
|
|
0.6981 0.019
|
|
0.7854 0.015
|
|
0.8727 0.012
|
|
1.0472 0.011
|
|
1.2217 0.009
|
|
1.3963 0.008
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/ClDr">
|
|
<description>Roll_moment_due_to_rudder</description>
|
|
<product>
|
|
<value>2</value>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>fcs/rudder-pos-rad</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.1745 0.0078
|
|
-0.0873 0.0070
|
|
0.0000 0.0059
|
|
0.0873 0.0043
|
|
0.1745 0.0023
|
|
0.2618 0.0007
|
|
0.3491 -0.0008
|
|
0.4363 0.0004
|
|
0.5236 0.0019
|
|
0.6109 0.0019
|
|
0.6981 0.0017
|
|
0.7854 0.0009
|
|
0.8727 0.0003
|
|
1.0472 0.0000
|
|
1.2217 0.0000
|
|
1.3963 0.0000
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
</axis>
|
|
|
|
<axis name="PITCH">
|
|
<function name="aero/coefficient/CmDh">
|
|
<description>Pitch_moment_due_to_horizontal_tail_deflection</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>
|
|
<independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
|
|
<tableData>
|
|
-0.5236 0.0 0.5236
|
|
-0.0873 0.3222 -0.0546 -0.4911
|
|
0.0000 0.3482 0.0000 -0.4729
|
|
0.0873 0.3897 0.0286 -0.4782
|
|
0.1745 0.3689 0.0156 -0.4988
|
|
0.2618 0.3975 0.0546 -0.4287
|
|
0.3491 0.3819 0.0442 -0.2722
|
|
0.4363 0.4131 0.0831 -0.1637
|
|
0.5236 0.4599 0.1377 -0.0546
|
|
0.6109 0.4443 0.1325 -0.0530
|
|
0.6981 0.3819 0.1013 -0.0650
|
|
0.7854 0.3585 0.0909 -0.0624
|
|
0.8727 0.3430 0.1299 -0.0364
|
|
1.0472 0.0208 -0.1117 -0.1975
|
|
1.2217 0.3248 -0.4521 -0.5144
|
|
|
|
</tableData>
|
|
</table>
|
|
<value>1.5</value>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/coefficient/CmDtv">
|
|
<description>Pitch_moment_due_to_thrust_vectoring</description>
|
|
<product>
|
|
<value>1.25</value>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/cbarw-ft</property>
|
|
<property>fcs/thrust-norm</property>
|
|
<table>
|
|
<independentVar lookup="row">aero/alpha-rad</independentVar>
|
|
<independentVar lookup="column">fcs/tvc-pos-rad</independentVar>
|
|
<tableData>
|
|
-0.3491 0.0 0.3491
|
|
-0.0873 0.4417 0.0 -0.7924
|
|
0.0000 0.4650 0.0 -0.8366
|
|
0.0873 0.4448 0.0 -0.8808
|
|
0.1745 0.4677 0.0 -0.8886
|
|
0.2618 0.4755 0.0 -0.8600
|
|
0.3491 0.4625 0.0 -0.7534
|
|
0.4363 0.4963 0.0 -0.6901
|
|
0.5236 0.4936 0.0 -0.6408
|
|
0.6109 0.4781 0.0 -0.6000
|
|
0.6981 0.5025 0.0 -0.5454
|
|
0.7854 0.5015 0.0 -0.5143
|
|
0.8727 0.4209 0.0 -0.5284
|
|
1.0472 0.4417 0.0 -0.5047
|
|
1.2217 0.2988 0.0 -0.4883
|
|
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Cma_M">
|
|
<description>Change_in_Pitch_moment_due_to_alpha_due_to_mach</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/cbarw-ft</property>
|
|
<property>aero/alpha-rad</property>
|
|
<table>
|
|
<independentVar>velocities/mach</independentVar>
|
|
<tableData>
|
|
0.6000 0.0000
|
|
0.8000 0.0974
|
|
0.9000 -0.3323
|
|
1.0000 -0.9626
|
|
1.1000 -0.8480
|
|
1.2000 -0.7907
|
|
</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>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.1750 -7.2100
|
|
-0.0870 -5.4000
|
|
0.0000 -5.2300
|
|
0.0870 -5.2600
|
|
0.1750 -6.1100
|
|
0.2620 -6.6400
|
|
0.3490 -5.6900
|
|
0.4360 -6.0000
|
|
0.5240 -6.2000
|
|
0.6110 -6.4000
|
|
0.6980 -6.6000
|
|
0.7850 -6.0000
|
|
</tableData>
|
|
</table>
|
|
</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>
|
|
<table>
|
|
<independentVar>velocities/mach</independentVar>
|
|
<tableData>
|
|
0.2570 -1.5611
|
|
1.8000 -2.0500
|
|
</tableData>
|
|
</table>
|
|
</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>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.349 0.0745
|
|
0.000 0.1780
|
|
0.873 0.0086
|
|
|
|
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Cnb_M">
|
|
<description>Change_in_Yaw_moment_due_to_beta_due_to_mach</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>aero/beta-rad</property>
|
|
<table>
|
|
<independentVar>velocities/mach</independentVar>
|
|
<tableData>
|
|
0.6000 0.0000
|
|
0.7000 -0.0688
|
|
0.8000 -0.0172
|
|
0.9000 0.0229
|
|
1.0000 0.0000
|
|
1.2000 -0.0688
|
|
1.4000 0.0057
|
|
1.6000 0.0688
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Cnbdot">
|
|
<description>Yaw_moment_due_to_beta_rate</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>aero/bi2vel</property>
|
|
<property>aero/betadot-rad_sec</property>
|
|
<value>-0.0115</value>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Cnp">
|
|
<description>Yaw_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>-0.0035</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>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.1750 -0.3800
|
|
-0.0870 -0.3630
|
|
0.0000 -0.3780
|
|
0.0870 -0.3860
|
|
0.1750 -0.3700
|
|
0.2620 -0.4530
|
|
0.3490 -0.5500
|
|
0.4360 -0.5820
|
|
0.5240 -0.5950
|
|
0.6110 -0.6370
|
|
0.6980 -1.0200
|
|
0.7850 -0.8400
|
|
</tableData>
|
|
</table>
|
|
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/CnDr">
|
|
<description>Yaw_moment_due_to_rudder</description>
|
|
<product>
|
|
<value>5</value>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>fcs/rudder-pos-rad</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
|
|
-0.1745 -0.048
|
|
-0.0873 -0.045
|
|
0.0000 -0.045
|
|
0.0873 -0.045
|
|
0.1745 -0.044
|
|
0.2618 -0.045
|
|
0.3491 -0.047
|
|
0.4363 -0.048
|
|
0.5236 -0.040
|
|
0.6109 -0.033
|
|
0.6981 -0.025
|
|
0.7854 -0.017
|
|
0.8727 -0.010
|
|
1.0472 -0.0075
|
|
1.2217 -0.0075
|
|
1.3963 -0.0075
|
|
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Cndr_M">
|
|
<description>Change_in_Yaw_moment_due_to_rudder_due_to_mach</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>aero/alpha-rad</property>
|
|
<property>fcs/rudder-pos-rad</property>
|
|
<table>
|
|
<independentVar>velocities/mach</independentVar>
|
|
<tableData>
|
|
0.6000 0.0000
|
|
1.2000 0.0401
|
|
1.6000 0.0716
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
<function name="aero/coefficient/Cnda">
|
|
<description>Adverse_yaw</description>
|
|
<product>
|
|
<value>2</value>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>fcs/left-aileron-pos-rad</property>
|
|
<table>
|
|
<independentVar>aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.1745 0.01
|
|
-0.0873 0.009
|
|
0.0000 0.010
|
|
0.0873 0.009
|
|
0.1745 0.008
|
|
0.2618 0.006
|
|
0.3491 -0.002
|
|
0.4363 -0.003
|
|
0.5236 -0.005
|
|
0.6109 -0.008
|
|
0.6981 -0.006
|
|
0.7854 -0.006
|
|
0.8727 -0.008
|
|
1.0472 -0.01
|
|
1.2217 -0.011
|
|
1.3963 -0.013
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
</axis>
|
|
</aerodynamics>
|
|
<!--
|
|
<output name="f16_datalog.csv" type="CSV" rate="1">
|
|
<property> aero/qbar-psf </property>
|
|
<property> attitude/phi-rad </property>
|
|
<property> position/h-sl-ft </property>
|
|
<property> velocities/vc-kts </property>
|
|
<property> fcs/throttle-cmd-norm </property>
|
|
<property> fcs/elevator-cmd-norm </property>
|
|
<property> fcs/pitch-trim-cmd-norm </property>
|
|
<property> propulsion/total-fuel-lbs </property>
|
|
<property> flight-path/gamma-rad </property>
|
|
<property> accelerations/n-pilot-z-norm </property>
|
|
<rates> ON </rates>
|
|
<velocities> ON </velocities>
|
|
<forces> ON </forces>
|
|
<moments> ON </moments>
|
|
<position> ON </position>
|
|
<fcs> ON </fcs>
|
|
<propulsion> OFF </propulsion>
|
|
<aerosurfaces> ON </aerosurfaces>
|
|
<fcs> ON </fcs>
|
|
<ground_reactions> ON </ground_reactions>
|
|
</output>
|
|
-->
|
|
</fdm_config>
|