1292 lines
36 KiB
XML
1292 lines
36 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="A320family" version="2.0" release="BETA"
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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> Bicyus (Jon Ortuondo) </author>
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<email> bicyus@gmail.com </email>
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<filecreationdate> 2012-02-15 </filecreationdate>
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<version> 0.99 </version>
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<description> Airbus A319-133 with IAE V2500 Engines </description>
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<note> Revised and fixed by Peter Brendt (jwocky) and Joshua Davidson (it0uchpods). Fork from the A320-Family aircraft project (Thanks to all authors) </note>
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<limitation></limitation>
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</fileheader>
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<metrics>
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<wingarea unit="FT2"> 1319.79 </wingarea>
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<wingspan unit="FT" > 111.26 </wingspan>
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<wing_incidence> 1.03 </wing_incidence>
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<chord unit="FT" > 13.76 </chord>
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<htailarea unit="FT2"> 334.24 </htailarea>
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<htailarm unit="FT" > 57.88 </htailarm>
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<vtailarea unit="FT2"> 248.79 </vtailarea>
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<vtailarm unit="FT" > 57.33 </vtailarm>
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<!-- location name="AERORP" unit="IN">
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<x> 642.122 </x>
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<y> 0 </y>
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<z> -25.2091 </z>
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</location -->
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<location name="AERORP" unit="IN">
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<x> 700.00 </x>
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<y> 0 </y>
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<z> 0.00 </z>
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</location>
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<location name="EYEPOINT" unit="IN">
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<x> 80 </x>
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<y> -30 </y>
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<z> 70 </z>
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</location>
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<location name="VRP" unit="IN">
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<x> 661.1 </x>
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<y> 0 </y>
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<z> -37 </z>
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</location>
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</metrics>
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<mass_balance>
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<ixx unit="SLUG*FT2"> 611903 </ixx>
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<iyy unit="SLUG*FT2"> 1735389 </iyy>
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<izz unit="SLUG*FT2"> 2301293 </izz>
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<!--
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___________________A320_________A330__________A340
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BOW_____________178000________270000________283925
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SPAN______________144___________198___________209
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LENGTH____________153___________209___________209
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ROLL MOI_________1725000______5727777_______10613448
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PITCH MOI________2550000______19040141_______13904249
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YAW MOI_________3950000______23089847_______24848934
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<ixx unit="SLUG*FT2"> 2262183 </ixx>
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<iyy unit="SLUG*FT2"> 3172439 </iyy>
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<izz unit="SLUG*FT2"> 3337024 </izz>
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<ixx unit="SLUG*FT2">1725000</ixx>
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<iyy unit="SLUG*FT2">2550000</iyy>
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<izz unit="SLUG*FT2">3950000</izz> -->
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<ixy unit="SLUG*FT2"> 0 </ixy>
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<ixz unit="SLUG*FT2"> 0 </ixz>
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<iyz unit="SLUG*FT2"> 0 </iyz>
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<emptywt unit="LBS">80431</emptywt> <!-- #ref-1 page 67, WV016. 90927lbs - 5248x2 (engines)=80431lbs-->
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<!-- #### PB: That makes no sense, the whole aircraft is 1479.1339 inches long. 650inches eqauls to about 43.95% MAC with the Airbus limits according to the AMM between 45% and 49%
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Also: The z-axis is -41.73 inches under the zero line of the plane while the pressure point is only -25,91 under the same line and slightly ahead, that causes the plane to behave quite unstable
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-->
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<!-- location name="CG" unit="IN">
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<! - -x> 642.122 </x- - >
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<x> 650.122 </x><! - - At zero load of fuel and cargo/pax the CG goes to 642 - - >
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<y> 0 </y>
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<z> -41.7398 </z>
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</location -->
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<location name="CG" unit="IN">
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<x> 652.00 </x>
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<y> 0 </y>
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<z> 0.00 </z>
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</location>
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<pointmass name="Cockpit Crew">
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<weight unit="LBS">400</weight> <!-- MAX: 400lbs, two pilots-->
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<location name="POINTMASS" unit="IN">
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<x>200</x>
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<y>0</y>
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<z>0</z>
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</location>
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</pointmass>
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<pointmass name="Cabin Crew">
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<weight unit="LBS">600</weight> <!-- MAX: 1320lbs, up to six flight-attendants-->
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<location name="POINTMASS" unit="IN">
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<x>696</x>
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<y>0</y>
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<z>0</z>
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</location>
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</pointmass>
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<pointmass name="PAX 0A (60 seats)">
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<weight unit="LBS">6600</weight> <!-- MAX: 13200lbs, 60 seats -->
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<location name="POINTMASS" unit="IN">
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<x>470.1711</x>
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<y>0</y>
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<z>0</z>
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</location>
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</pointmass>
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<pointmass name="PAX 0B (60 seats)">
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<weight unit="LBS">6600</weight> <!-- MAX: 13200lbs, 60 seats -->
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<location name="POINTMASS" unit="IN">
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<x>809.5669</x>
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<y>0</y>
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<z>0</z>
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</location>
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</pointmass>
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<pointmass name="PAX 0C (54 seats)">
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<weight unit="LBS">5940</weight> <!-- MAX: 11880lbs, 54 seats -->
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<location name="POINTMASS" unit="IN">
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<x>1163.2729</x>
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<y>0</y>
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<z>0</z>
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</location>
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</pointmass>
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<pointmass name="Cargo Hold 1">
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<weight unit="LBS">2000</weight> <!-- MAX: 7500.126lbs -->
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<location name="POINTMASS" unit="IN">
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<x>383.4792</x>
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<y>0</y>
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<z>-29.5</z> <!-- 1.5m and now half of it for the center point of the load -->
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</location>
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</pointmass>
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<!-- Cargo Hold 2 doesn't exist, that is the center tank -->
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<pointmass name="Cargo Hold 3">
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<weight unit="LBS">2000</weight> <!-- MAX: 5384.414lbs -->
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<location name="POINTMASS" unit="IN">
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<x>849.1324</x>
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<y>0</y>
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<z>-29.5</z>
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</location>
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</pointmass>
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<pointmass name="Cargo Hold 4">
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<weight unit="LBS">1500</weight> <!-- MAX: 4651.754lbs -->
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<location name="POINTMASS" unit="IN">
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<x>931.0653</x>
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<y>0</y>
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<z>-29.5</z>
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</location>
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</pointmass>
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<pointmass name="Cargo Hold 5">
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<weight unit="LBS">2000</weight> <!-- MAX: 3300.320lbs -->
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<location name="POINTMASS" unit="IN">
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<x>1068.2634</x>
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<y>0</y>
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<z>0</z> <!-- Cargo Hold #5 sits higher on the range of the cabin deck, it's only loadable with lifter -->
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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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<!-- REF-1 page 165 + 271 -->
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<contact type="BOGEY" name="NOSE_LG">
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<location unit="IN">
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<x> 197.6772 </x>
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<y> 0 </y>
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<z> -137.9617 </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"> 30935.5 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 16978.5 </damping_coeff>
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<max_steer unit="DEG"> 70 </max_steer> <!-- REF-1 page 133 -->
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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> 699.9243 </x>-->
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<x> 695.3149 </x>
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<y> -149.4094 </y>
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<z> -150.4824 </z>
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</location>
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<!-- <static_friction> 0.5 </static_friction> WHAT??? less static than dinamyc friction?-->
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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"> 59785 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 23957 </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> 697.3425 </x> It should be right left simetric
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<x> 699.9243 </x> -->
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<x> 695.3149 </x>
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<y> 149.4094 </y>
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<z> -150.4824 </z>
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</location>
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<!-- <static_friction> 0.5 </static_friction> WHAT??? less static than dinamyc friction?-->
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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"> 169785 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff-->
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<spring_coeff unit="LBS/FT"> 59785 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 23957 </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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<contact type="STRUCTURE" name="NOSE_1">
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<location unit="IN">
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<x> 37.7953 </x>
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<y> 0 </y>
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<z> -38.1374 </z>
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</location>
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<static_friction> 1.0 </static_friction>
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<dynamic_friction> 0.4 </dynamic_friction>
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<rolling_friction> 0.4 </rolling_friction>
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<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
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|
<max_steer unit="DEG"> 0.0 </max_steer>
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|
<brake_group> NONE </brake_group>
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|
<retractable>0</retractable>
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|
</contact>
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<contact type="STRUCTURE" name="NOSE_2">
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<location unit="IN">
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<x> 128.1102 </x>
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<y> 0 </y>
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<z> -55.0271 </z>
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</location>
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<static_friction> 1.0 </static_friction>
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|
<dynamic_friction> 0.4 </dynamic_friction>
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|
<rolling_friction> 0.4 </rolling_friction>
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|
<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
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|
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
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|
<max_steer unit="DEG"> 0.0 </max_steer>
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|
<brake_group> NONE </brake_group>
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|
<retractable>0</retractable>
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|
</contact>
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<contact type="STRUCTURE" name="CENTER_1">
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<location unit="IN">
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<x> 274.0157 </x>
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<y> 0 </y>
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<z> -60.0665 </z>
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</location>
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|
<static_friction> 1.0 </static_friction>
|
|
<dynamic_friction> 0.4 </dynamic_friction>
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|
<rolling_friction> 0.4 </rolling_friction>
|
|
<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
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|
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
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|
<max_steer unit="DEG"> 0.0 </max_steer>
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|
<brake_group> NONE </brake_group>
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|
<retractable>0</retractable>
|
|
</contact>
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<contact type="STRUCTURE" name="CENTER_2">
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<location unit="IN">
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<x> 930 </x>
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<y> 0 </y>
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<z> -60.0665 </z>
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</location>
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|
<static_friction> 1.0 </static_friction>
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|
<dynamic_friction> 0.4 </dynamic_friction>
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|
<rolling_friction> 0.4 </rolling_friction>
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|
<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
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|
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
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|
<max_steer unit="DEG"> 0.0 </max_steer>
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|
<brake_group> NONE </brake_group>
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|
<retractable>0</retractable>
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|
</contact>
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<contact type="STRUCTURE" name="ENG_1">
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<location unit="IN">
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<x>589.735</x>
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<y>-226.575</y>
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<z>-95.567</z>
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</location>
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|
<static_friction> 1.0 </static_friction>
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|
<dynamic_friction> 0.4 </dynamic_friction>
|
|
<rolling_friction> 0.4 </rolling_friction>
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|
<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
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|
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
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|
<max_steer unit="DEG"> 0.0 </max_steer>
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|
<brake_group> NONE </brake_group>
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|
<retractable>0</retractable>
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|
</contact>
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<contact type="STRUCTURE" name="ENG_2">
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<location unit="IN">
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<x>589.735</x>
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|
<y>226.575</y>
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|
<z>-95.567</z>
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</location>
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|
<static_friction> 1.0 </static_friction>
|
|
<dynamic_friction> 0.5 </dynamic_friction>
|
|
<rolling_friction> 0.4 </rolling_friction>
|
|
<spring_coeff unit="LBS/FT"> 50000 </spring_coeff>
|
|
<damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
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|
<max_steer unit="DEG"> 0.0 </max_steer>
|
|
<brake_group> NONE </brake_group>
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|
<retractable>0</retractable>
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|
</contact>
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|
|
|
|
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<contact type="STRUCTURE" name="TAIL_1">
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|
<location unit="IN">
|
|
<x> 1097.9921 </x>
|
|
<y> 0 </y>
|
|
<z> -44.7722 </z>
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|
</location>
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|
<static_friction> 1.0 </static_friction>
|
|
<dynamic_friction> 0.4 </dynamic_friction>
|
|
<rolling_friction> 0.4 </rolling_friction>
|
|
<spring_coeff unit="LBS/FT"> 50000 </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="TAIL_2">
|
|
<location unit="IN">
|
|
<x> 1225 </x>
|
|
<y> 0 </y>
|
|
<z> -18.8067 </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"> 50000 </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="TAIL_3">
|
|
<location unit="IN">
|
|
<x> 1341.6142 </x>
|
|
<y> 0 </y>
|
|
<z> -10.2599 </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"> 50000 </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="TAIL_4">
|
|
<location unit="IN">
|
|
<x> 1469.0945 </x>
|
|
<y> 0 </y>
|
|
<z> 47.4138 </z>
|
|
</location>
|
|
<static_friction> 1.0 </static_friction>
|
|
<dynamic_friction> 1 </dynamic_friction>
|
|
<rolling_friction> 1 </rolling_friction>
|
|
<spring_coeff unit="LBS/FT"> 50000 </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="WING_TIP_1">
|
|
<location unit="IN">
|
|
<x> 838.8898 </x>
|
|
<y> -667.5197 </y>
|
|
<z> 35.7926 </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"> 50000 </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="WING_TIP_2">
|
|
<location unit="IN">
|
|
<x> 838.8898 </x>
|
|
<y> 667.5197 </y>
|
|
<z> 35.7926 </z>
|
|
</location>
|
|
<static_friction> 1.0 </static_friction>
|
|
<dynamic_friction> 1 </dynamic_friction>
|
|
<rolling_friction> 1 </rolling_friction>
|
|
<spring_coeff unit="LBS/FT"> 50000 </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="v2527_a5">
|
|
<location unit="IN">
|
|
<x> 620.0683 </x>
|
|
<y> -226.575 </y>
|
|
<z> -45.567 </z>
|
|
</location>
|
|
<orient unit="DEG">
|
|
<roll> 0.0 </roll>
|
|
<pitch> 2.2 </pitch>
|
|
<yaw> 1 </yaw>
|
|
</orient>
|
|
<feed>3</feed>
|
|
<feed>1</feed>
|
|
<feed>2</feed>
|
|
<thruster file="direct">
|
|
<location unit="IN">
|
|
<x> 655.4820 </x>
|
|
<y> -226.575 </y>
|
|
<z> 0.000 </z>
|
|
</location>
|
|
<orient unit="DEG">
|
|
<roll> 0.0 </roll>
|
|
<pitch> 2.2 </pitch>
|
|
<yaw> 1 </yaw>
|
|
</orient>
|
|
</thruster>
|
|
</engine>
|
|
|
|
<engine file="v2527_a5">
|
|
<location unit="IN">
|
|
<x> 620.0683 </x>
|
|
<y> 226.575 </y>
|
|
<z> -45.567 </z>
|
|
</location>
|
|
<orient unit="DEG">
|
|
<roll> 0.0 </roll>
|
|
<pitch> 2.2 </pitch>
|
|
<yaw> -1 </yaw>
|
|
</orient>
|
|
<feed>3</feed>
|
|
<feed>5</feed>
|
|
<feed>4</feed>
|
|
<thruster file="direct">
|
|
<location unit="IN">
|
|
<x> 655.4820 </x>
|
|
<y> 226.575 </y>
|
|
<z> 0.000 </z>
|
|
</location>
|
|
<orient unit="DEG">
|
|
<roll> 0.0 </roll>
|
|
<pitch> 2.2 </pitch>
|
|
<yaw> -1 </yaw>
|
|
</orient>
|
|
</thruster>
|
|
</engine>
|
|
|
|
|
|
<tank type="FUEL"> <!-- Left Tank (Wing tip Ventilation Surge) 0 -->
|
|
<location unit="IN">
|
|
<x> 783.0709 </x>
|
|
<y> -574.4148 </y>
|
|
<z> 3.1080 </z>
|
|
</location>
|
|
<capacity unit="LBS"> 412 </capacity><!-- need review --> <!-- would be 1 percent of max load per each wing, 412 each. Needs temp rise of 20C at max load to fill -->
|
|
<contents unit="LBS"> 0 </contents>
|
|
|
|
<priority>4</priority>
|
|
<type>JET-A1</type>
|
|
<temperature>50</temperature>
|
|
</tank>
|
|
<tank type="FUEL"> <!-- Left Tank (Outer) 1 -->
|
|
<location unit="IN">
|
|
<x> 739.5669 </x>
|
|
<y> -457.4259 </y>
|
|
<z> -8.0898 </z>
|
|
</location>
|
|
<capacity unit="LBS"> 1520.00 </capacity><!-- need review -->
|
|
<contents unit="LBS"> 1520 </contents><!-- outer filled first than inner -->
|
|
<standpipe unit="LBS">21</standpipe><!-- minimun fuel on pipes -->
|
|
<priority>2</priority>
|
|
<type>JET-A1</type>
|
|
<temperature>50</temperature>
|
|
</tank>
|
|
<tank type="FUEL"> <!-- Left Tank (Inner) 2 -->
|
|
<location unit="IN">
|
|
<x> 652.5591 </x>
|
|
<y> -236.2992 </y>
|
|
<z> -33.9470 </z>
|
|
</location>
|
|
<capacity unit="LBS"> 11982 </capacity><!-- correct by FCOM -->
|
|
<contents unit="LBS"> 4480 </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 3 -->
|
|
<location unit="IN">
|
|
<x> 522.0473 </x>
|
|
<y> 0 </y>
|
|
<z> -47.0 </z>
|
|
</location>
|
|
<capacity unit="LBS"> 14281 </capacity><!-- correct by FCOM -->
|
|
<contents unit="LBS"> 0 </contents> <!-- wing tanks always filled first -->
|
|
<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) 4 -->
|
|
<location unit="IN">
|
|
<x> 652.5591 </x>
|
|
<y> 236.2992 </y>
|
|
<z> -33.9470 </z>
|
|
</location>
|
|
<capacity unit="LBS"> 11982 </capacity><!-- correct by FCOM -->
|
|
<contents unit="LBS"> 4480 </contents>
|
|
<standpipe unit="LBS">31</standpipe><!-- minimum fuel on pipes -->
|
|
<priority>3</priority>
|
|
<type>JET-A1</type>
|
|
<temperature>50</temperature>
|
|
</tank>
|
|
<tank type="FUEL"> <!-- Right Tank (Outer) 5 -->
|
|
<location unit="IN">
|
|
<x> 739.5669 </x>
|
|
<y> 457.4259 </y>
|
|
<z> -8.0898 </z>
|
|
</location>
|
|
<capacity unit="LBS"> 1520 </capacity><!-- correct by FCOM -->
|
|
<contents unit="LBS"> 1520 </contents><!-- outer filled before inner -->
|
|
<standpipe unit="LBS">21</standpipe><!-- minimun fuel on pipes -->
|
|
<priority>2</priority>
|
|
<type>JET-A1</type>
|
|
<temperature>50</temperature>
|
|
</tank>
|
|
<tank type="FUEL"> <!-- Right Tank (Wing tip Ventilation Surge) 6 -->
|
|
<location unit="IN">
|
|
<x> 783.0709 </x>
|
|
<y> 574.4148 </y>
|
|
<z> 3.1080 </z>
|
|
</location>
|
|
<capacity unit="LBS"> 412 </capacity><!-- need review --> <!-- 1 percent of max, see left surge tank, is 412 lb each -->
|
|
<contents unit="LBS"> 0 </contents>
|
|
<priority>4</priority>
|
|
<type>JET-A1</type>
|
|
<temperature>50</temperature>
|
|
</tank>
|
|
</propulsion>
|
|
|
|
<system file="pushback" />
|
|
<!--system file="a320-fuel" /-->
|
|
<system file="glass-effect1" />
|
|
<system file="it-fbw" />
|
|
<system file="fmgc" />
|
|
|
|
<flight_control name="FCS: A320">
|
|
<channel name="Pitch">
|
|
<summer name="Pitch Trim Sum">
|
|
<input>/controls/flight/elevator-sum</input>
|
|
<input>/controls/flight/elevator-trim</input>
|
|
<clipto>
|
|
<min>-1</min>
|
|
<max>1</max>
|
|
</clipto>
|
|
</summer>
|
|
|
|
<aerosurface_scale name="Elevator Control">
|
|
<input>fcs/pitch-trim-sum</input>
|
|
<gain>0.015</gain>
|
|
<range>
|
|
<min>-20</min>
|
|
<max>20</max>
|
|
</range>
|
|
<output>fcs/elevator-pos-rad</output>
|
|
</aerosurface_scale>
|
|
<aerosurface_scale name="Elevator Position Normalizer">
|
|
<input>fcs/pitch-trim-sum</input>
|
|
<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>/controls/flight/aileron-sum</input>
|
|
<input>/controls/flight/aileron-trim</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>-15</min>
|
|
<max>15</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>-15</min>
|
|
<max>15</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>-15</min>
|
|
<max>15</max>
|
|
</domain>
|
|
<range>
|
|
<min>-1</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>-15</min>
|
|
<max>15</max>
|
|
</domain>
|
|
<range>
|
|
<min>-1</min>
|
|
<max>1</max>
|
|
</range>
|
|
<output>fcs/right-aileron-pos-norm</output>
|
|
</aerosurface_scale>
|
|
</channel>
|
|
<channel name="Throttle">
|
|
<pure_gain name="fcs/throttle1">
|
|
<input>/controls/engines/engine[0]/throttle-fdm</input>
|
|
<gain>1</gain>
|
|
<output>fcs/throttle-cmd-norm</output>
|
|
<output>fcs/throttle-pos-norm</output>
|
|
</pure_gain>
|
|
<pure_gain name="fcs/throttle2">
|
|
<input>/controls/engines/engine[1]/throttle-fdm</input>
|
|
<gain>1</gain>
|
|
<output>fcs/throttle-cmd-norm[1]</output>
|
|
<output>fcs/throttle-pos-norm[1]</output>
|
|
</pure_gain>
|
|
</channel>
|
|
|
|
<channel name="Yaw">
|
|
<pure_gain name="fcs/rudder-cmd">
|
|
<input>/controls/flight/rudder-fdm</input>
|
|
<gain>-1</gain>
|
|
<output>fcs/rudder-cmd-norm</output>
|
|
</pure_gain>
|
|
|
|
<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>/controls/flight/flaps</input>
|
|
<traverse>
|
|
<setting>
|
|
<position>0</position>
|
|
<time>0</time>
|
|
</setting>
|
|
<setting>
|
|
<position>35</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>35</max>
|
|
</domain>
|
|
<range>
|
|
<min>0</min>
|
|
<max>1</max>
|
|
</range>
|
|
<output>fcs/flap-pos-norm</output>
|
|
</aerosurface_scale>
|
|
|
|
</channel>
|
|
|
|
<channel name="Slats">
|
|
|
|
<kinematic name="Slats Control">
|
|
<input>/controls/flight/slats</input>
|
|
<traverse>
|
|
<setting>
|
|
<position>0</position>
|
|
<time>0</time>
|
|
</setting>
|
|
<setting>
|
|
<position>27</position>
|
|
<time>30</time>
|
|
</setting>
|
|
</traverse>
|
|
<output>fcs/slat-pos-deg</output>
|
|
</kinematic>
|
|
|
|
<aerosurface_scale name="Slat position normalized">
|
|
<input>fcs/slat-pos-deg</input>
|
|
<domain>
|
|
<min>0</min>
|
|
<max>27</max>
|
|
</domain>
|
|
<range>
|
|
<min>0</min>
|
|
<max>1</max>
|
|
</range>
|
|
<output>fcs/slat-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>1</time>
|
|
</setting>
|
|
</traverse>
|
|
<output>fcs/speedbrake-pos-norm</output>
|
|
</kinematic>
|
|
</channel>
|
|
|
|
<channel name="Tiller">
|
|
|
|
<switch name="/controls/gear/tiller-disabled">
|
|
<default value="0"/>
|
|
<test logic="AND" value="1">
|
|
/controls/gear/tiller-enabled == 0
|
|
</test>
|
|
</switch>
|
|
|
|
<fcs_function name="Nose Wheel Steering 0">
|
|
<function name="fcs/steer-nose-deg[0]">
|
|
<description>Steering command for nose gear</description>
|
|
<sum>
|
|
<product>
|
|
<table>
|
|
<independentVar lookup="row">/controls/gear/tiller-cmd-norm</independentVar>
|
|
<independentVar lookup="column">/controls/flight/rudder</independentVar>
|
|
<tableData>
|
|
-1 0 1
|
|
-1 -70 -70 -70
|
|
0 -7 0 7
|
|
1 70 70 70
|
|
</tableData>
|
|
</table>
|
|
<property>/controls/gear/tiller-enabled</property>
|
|
</product>
|
|
<product>
|
|
<product>
|
|
<property>/controls/flight/rudder</property>
|
|
<value>70</value>
|
|
</product>
|
|
<property>/controls/gear/tiller-disabled</property>
|
|
</product>
|
|
</sum>
|
|
</function>
|
|
</fcs_function>
|
|
|
|
<!-- simulate rotational friction -->
|
|
<actuator name="Gear Nose Actuator">
|
|
<input>fcs/steer-nose-deg[0]</input>
|
|
<rate_limit>70</rate_limit>
|
|
<output>fcs/steer-pos-deg[0]</output>
|
|
</actuator>
|
|
|
|
</channel>
|
|
|
|
|
|
</flight_control>
|
|
|
|
|
|
<aerodynamics>
|
|
|
|
<axis name="LIFT">
|
|
|
|
<function name="aero/force/Lift_alpha">
|
|
<description>Lift due to alpha</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<table>
|
|
<independentVar lookup="row">aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-0.20 -0.900
|
|
0.00 0.103
|
|
0.15 1.600
|
|
0.23 1.900
|
|
0.60 1.000
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/force/Lift_flap">
|
|
<description>Delta Lift due to flaps</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<table>
|
|
<independentVar lookup="row">fcs/flap-pos-norm</independentVar>
|
|
<tableData>
|
|
0.000 0.00000
|
|
0.290 0.00250
|
|
0.596 0.00700
|
|
0.645 0.01300
|
|
1.000 0.01700
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/force/Lift_slats">
|
|
<description>Delta Lift due to slats</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>fcs/slat-pos-deg</property>
|
|
<value> 0.01000 </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>
|
|
|
|
<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>0.04</value>
|
|
</product>
|
|
</function>
|
|
|
|
</axis>
|
|
|
|
<axis name="DRAG">
|
|
|
|
<function name="aero/force/Drag_basic">
|
|
<description>Drag at zero lift</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<table>
|
|
<independentVar lookup="row">aero/alpha-rad</independentVar>
|
|
<tableData>
|
|
-1.57 1.300
|
|
-0.26 0.021
|
|
0.00 0.012
|
|
0.26 0.028
|
|
1.57 1.350
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/force/Drag_induced">
|
|
<description>Induced drag</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>aero/cl-squared</property>
|
|
<value>0.041</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>
|
|
|
|
<function name="aero/force/Drag_flap">
|
|
<description>Drag due to flaps</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>fcs/flap-pos-deg</property>
|
|
<value> 0.00120 </value>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/force/Drag_slats">
|
|
<description>Drag due to slats</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>fcs/flap-pos-deg</property>
|
|
<value> 0.00200 </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>0.030</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>0.03</value>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/force/Drag_beta">
|
|
<description>Drag due to sideslip</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<table>
|
|
<independentVar lookup="row">aero/beta-rad</independentVar>
|
|
<tableData>
|
|
-1.57 1.230
|
|
-0.26 0.050
|
|
0.00 0.000
|
|
0.26 0.050
|
|
1.57 1.230
|
|
</tableData>
|
|
</table>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/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>0.045</value>
|
|
</product>
|
|
</function>
|
|
|
|
</axis>
|
|
|
|
<axis name="SIDE">
|
|
|
|
<function name="aero/force/Side_beta">
|
|
<description>Side force due to beta</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>aero/beta-rad</property>
|
|
<value>-1</value>
|
|
</product>
|
|
</function>
|
|
|
|
</axis>
|
|
|
|
<axis name="ROLL">
|
|
|
|
<function name="aero/moment/Roll_beta">
|
|
<description>Roll moment due to beta</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>aero/beta-rad</property>
|
|
<value>-0.1</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>-0.95</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/moment/Roll_aileron">
|
|
<description>Roll moment due to aileron</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>fcs/left-aileron-pos-rad</property>
|
|
<value>0.20</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>0.003</value>
|
|
</product>
|
|
</function>
|
|
|
|
</axis>
|
|
|
|
<axis name="PITCH">
|
|
|
|
<function name="aero/moment/Pitch_alpha">
|
|
<description>Pitch moment due to alpha</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/cbarw-ft</property>
|
|
<property>aero/alpha-rad</property>
|
|
<value>-0.6</value>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/moment/Pitch_elevator">
|
|
<description>Pitch moment due to elevator</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/cbarw-ft</property>
|
|
<property>fcs/elevator-pos-rad</property>
|
|
<table>
|
|
<independentVar lookup="row">velocities/mach</independentVar>
|
|
<tableData>
|
|
0.0 -1.900
|
|
2.0 -0.900
|
|
</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>-140</value>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/moment/Pitch_alphadot">
|
|
<description>Pitch moment due to alpha rate</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/cbarw-ft</property>
|
|
<property>aero/ci2vel</property>
|
|
<property>aero/alphadot-rad_sec</property>
|
|
<value>-1</value>
|
|
</product>
|
|
</function>
|
|
|
|
</axis>
|
|
|
|
<axis name="YAW">
|
|
|
|
<function name="aero/moment/Yaw_beta">
|
|
<description>Yaw moment due to beta</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>aero/beta-rad</property>
|
|
<value>0.12</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>-0.2</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="pushback" frame="BODY">
|
|
<location unit="IN">
|
|
<x>294</x>
|
|
<y>0</y>
|
|
<z>-149</z>
|
|
</location>
|
|
<direction>
|
|
<x>1</x>
|
|
<y>0</y>
|
|
<z>0</z>
|
|
</direction>
|
|
</force>
|
|
</external_reactions>
|
|
</fdm_config>
|