2017-04-03 17:56:46 +00:00
<?xml version="1.0"?>
2016-12-07 18:05:28 +00:00
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name= "A320family" version= "2.0" release= "BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader >
<author > Bicyus (Jon Ortuondo) </author>
<email > bicyus@gmail.com </email>
<filecreationdate > 2012-02-15 </filecreationdate>
<version > 0.99 </version>
<description > Airbus ACJ with IAE V2500 Engines </description>
<note > Revised and fixed by Peter Brendt (jwocky) and Joshua Davidson (it0uchpods). Fork from the A320-Family aircraft project (Thanks to all authors) </note>
<limitation > </limitation>
</fileheader>
<metrics >
<wingarea unit= "FT2" > 1319.79 </wingarea>
<wingspan unit= "FT" > 111.26 </wingspan>
<wing_incidence > 1.03 </wing_incidence>
<chord unit= "FT" > 13.76 </chord>
<htailarea unit= "FT2" > 334.24 </htailarea>
<htailarm unit= "FT" > 57.88 </htailarm>
<vtailarea unit= "FT2" > 248.79 </vtailarea>
<vtailarm unit= "FT" > 57.33 </vtailarm>
<!-- location name="AERORP" unit="IN">
<x > 642.122 </x>
<y > 0 </y>
<z > -25.2091 </z>
< /location -->
<location name= "AERORP" unit= "IN" >
2017-04-07 18:09:40 +00:00
<x > 700.00 </x>
2016-12-07 18:05:28 +00:00
<y > 0 </y>
<z > 0.00 </z>
</location>
<location name= "EYEPOINT" unit= "IN" >
<x > 80 </x>
<y > -30 </y>
<z > 70 </z>
</location>
<location name= "VRP" unit= "IN" >
<x > 661.1 </x>
<y > 0 </y>
<z > -37 </z>
</location>
</metrics>
<mass_balance >
<ixx unit= "SLUG*FT2" > 611903 </ixx>
<iyy unit= "SLUG*FT2" > 1735389 </iyy>
<izz unit= "SLUG*FT2" > 2301293 </izz>
<!--
___________________A320_________A330__________A340
BOW_____________178000________270000________283925
SPAN______________144___________198___________209
LENGTH____________153___________209___________209
ROLL MOI_________1725000______5727777_______10613448
PITCH MOI________2550000______19040141_______13904249
YAW MOI_________3950000______23089847_______24848934
<ixx unit= "SLUG*FT2" > 2262183 </ixx>
<iyy unit= "SLUG*FT2" > 3172439 </iyy>
<izz unit= "SLUG*FT2" > 3337024 </izz>
<ixx unit= "SLUG*FT2" > 1725000</ixx>
<iyy unit= "SLUG*FT2" > 2550000</iyy>
<izz unit= "SLUG*FT2" > 3950000</izz> -->
<ixy unit= "SLUG*FT2" > 0 </ixy>
<ixz unit= "SLUG*FT2" > 0 </ixz>
<iyz unit= "SLUG*FT2" > 0 </iyz>
<emptywt unit= "LBS" > 80431</emptywt> <!-- #ref - 1 page 67, WV016. 90927lbs - 5248x2 (engines)=80431lbs -->
<!-- #### 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%
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
-->
<!-- location name="CG" unit="IN">
<! - -x> 642.122 < /x- - >
<x > 650.122 </x> <! - - At zero load of fuel and cargo/pax the CG goes to 642 - - >
<y > 0 </y>
<z > -41.7398 </z>
< /location -->
<location name= "CG" unit= "IN" >
2017-04-07 18:09:40 +00:00
<x > 652.00 </x>
2016-12-07 18:05:28 +00:00
<y > 0 </y>
<z > 0.00 </z>
</location>
<pointmass name= "Cockpit Crew" >
<weight unit= "LBS" > 400</weight> <!-- MAX: 400lbs, two pilots -->
<location name= "POINTMASS" unit= "IN" >
<x > 200</x>
<y > 0</y>
<z > 0</z>
</location>
</pointmass>
<pointmass name= "Cabin Crew" >
<weight unit= "LBS" > 600</weight> <!-- MAX: 1320lbs, up to six flight - attendants -->
<location name= "POINTMASS" unit= "IN" >
<x > 696</x>
<y > 0</y>
<z > 0</z>
</location>
</pointmass>
<pointmass name= "PAX 0A (60 seats)" >
<weight unit= "LBS" > 6600</weight> <!-- MAX: 13200lbs, 60 seats -->
<location name= "POINTMASS" unit= "IN" >
<x > 470.1711</x>
<y > 0</y>
<z > 0</z>
</location>
</pointmass>
<pointmass name= "PAX 0B (60 seats)" >
<weight unit= "LBS" > 6600</weight> <!-- MAX: 13200lbs, 60 seats -->
<location name= "POINTMASS" unit= "IN" >
<x > 809.5669</x>
<y > 0</y>
<z > 0</z>
</location>
</pointmass>
<pointmass name= "PAX 0C (54 seats)" >
<weight unit= "LBS" > 5940</weight> <!-- MAX: 11880lbs, 54 seats -->
<location name= "POINTMASS" unit= "IN" >
<x > 1163.2729</x>
<y > 0</y>
<z > 0</z>
</location>
</pointmass>
<pointmass name= "Cargo Hold 1" >
<weight unit= "LBS" > 2000</weight> <!-- MAX: 7500.126lbs -->
<location name= "POINTMASS" unit= "IN" >
<x > 383.4792</x>
<y > 0</y>
<z > -29.5</z> <!-- 1.5m and now half of it for the center point of the load -->
</location>
</pointmass>
<!-- Cargo Hold 2 doesn't exist, that is the center tank -->
<pointmass name= "Cargo Hold 3" >
<weight unit= "LBS" > 2000</weight> <!-- MAX: 5384.414lbs -->
<location name= "POINTMASS" unit= "IN" >
<x > 849.1324</x>
<y > 0</y>
<z > -29.5</z>
</location>
</pointmass>
<pointmass name= "Cargo Hold 4" >
<weight unit= "LBS" > 1500</weight> <!-- MAX: 4651.754lbs -->
<location name= "POINTMASS" unit= "IN" >
<x > 931.0653</x>
<y > 0</y>
<z > -29.5</z>
</location>
</pointmass>
<pointmass name= "Cargo Hold 5" >
<weight unit= "LBS" > 2000</weight> <!-- MAX: 3300.320lbs -->
<location name= "POINTMASS" unit= "IN" >
<x > 1068.2634</x>
<y > 0</y>
<z > 0</z> <!-- Cargo Hold #5 sits higher on the range of the cabin deck, it's only loadable with lifter -->
</location>
</pointmass>
</mass_balance>
<ground_reactions >
<!-- REF - 1 page 165 + 271 -->
<contact type= "BOGEY" name= "NOSE_LG" >
<location unit= "IN" >
<x > 197.6772 </x>
<y > 0 </y>
<z > -137.9617 </z>
</location>
<static_friction > 0.8 </static_friction>
<dynamic_friction > 0.5 </dynamic_friction>
<rolling_friction > 0.02 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 30935.5 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 16978.5 </damping_coeff>
<max_steer unit= "DEG" > 70 </max_steer> <!-- REF - 1 page 133 -->
<brake_group > NONE </brake_group>
<retractable > 1</retractable>
</contact>
<contact type= "BOGEY" name= "LEFT_MLG" >
<location unit= "IN" >
<!-- <x> 699.9243 </x> -->
<x > 695.3149 </x>
<y > -149.4094 </y>
<z > -150.4824 </z>
</location>
<!-- <static_friction> 0.5 </static_friction> WHAT??? less static than dinamyc friction? -->
<static_friction > 0.8 </static_friction>
<dynamic_friction > 0.5 </dynamic_friction>
<rolling_friction > 0.02 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 59785 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 23957 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > LEFT </brake_group>
<retractable > 1</retractable>
</contact>
<contact type= "BOGEY" name= "RIGHT_MLG" >
<location unit= "IN" >
<!-- <x> 697.3425 </x> It should be right left simetric
<x > 699.9243 </x> -->
<x > 695.3149 </x>
<y > 149.4094 </y>
<z > -150.4824 </z>
</location>
<!-- <static_friction> 0.5 </static_friction> WHAT??? less static than dinamyc friction? -->
<static_friction > 0.8 </static_friction>
<dynamic_friction > 0.5 </dynamic_friction>
<rolling_friction > 0.02 </rolling_friction>
<!-- spring_coeff unit="LBS/FT"> 169785 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 33957 </damping_coeff-->
<spring_coeff unit= "LBS/FT" > 59785 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 23957 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > RIGHT </brake_group>
<retractable > 1</retractable>
</contact>
<contact type= "STRUCTURE" name= "NOSE_1" >
<location unit= "IN" >
<x > 37.7953 </x>
<y > 0 </y>
<z > -38.1374 </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= "NOSE_2" >
<location unit= "IN" >
<x > 128.1102 </x>
<y > 0 </y>
<z > -55.0271 </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= "CENTER_1" >
<location unit= "IN" >
<x > 274.0157 </x>
<y > 0 </y>
<z > -60.0665 </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= "CENTER_2" >
<location unit= "IN" >
<x > 930 </x>
<y > 0 </y>
<z > -60.0665 </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= "ENG_1" >
<location unit= "IN" >
<x > 589.735</x>
<y > -226.575</y>
<z > -95.567</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= "ENG_2" >
<location unit= "IN" >
<x > 589.735</x>
<y > 226.575</y>
<z > -95.567</z>
</location>
<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>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "TAIL_1" >
<location unit= "IN" >
<x > 1097.9921 </x>
<y > 0 </y>
<z > -44.7722 </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_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" >
2017-05-07 19:26:41 +00:00
<x > 620.0683 </x>
2016-12-07 18:05:28 +00:00
<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>
2017-02-25 12:30:45 +00:00
<capacity unit= "LBS" > 412 </capacity> <!-- 1 percent of total capacity, needs 20C to be filled -->
2016-12-07 18:05:28 +00:00
<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>
2017-02-25 12:30:45 +00:00
<capacity unit= "LBS" > 1520.00 </capacity> <!-- correct by FCOM -->
<contents unit= "LBS" > 1520 </contents> <!-- outer filled first than inner -->
2016-12-07 18:05:28 +00:00
<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>
2017-02-25 12:30:45 +00:00
<capacity unit= "LBS" > 11982 </capacity> <!-- correct by FCOM -->
2017-05-08 01:34:45 +00:00
<contents unit= "LBS" > 4480 </contents>
2016-12-07 18:05:28 +00:00
<standpipe unit= "LBS" > 31</standpipe> <!-- minimun fuel on pipes -->
<priority > 3</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
2017-02-25 12:30:45 +00:00
<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 filled first -->
<standpipe unit= "LBS" > 43</standpipe> <!-- minimun fuel on pipes -->
<priority > 1</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
2016-12-07 18:05:28 +00:00
<tank type= "FUEL" > <!-- Right Tank (Inner) 4 -->
<location unit= "IN" >
<x > 652.5591 </x>
<y > 236.2992 </y>
<z > -33.9470 </z>
</location>
2017-02-25 12:30:45 +00:00
<capacity unit= "LBS" > 11982 </capacity> <!-- correct by FCOM -->
2017-05-08 01:34:45 +00:00
<contents unit= "LBS" > 4480 </contents>
2016-12-07 18:05:28 +00:00
<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> <!-- need review -->
2017-02-25 12:30:45 +00:00
<contents unit= "LBS" > 1520 </contents> <!-- outer tank filled first than inner tank -->
2016-12-07 18:05:28 +00:00
<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>
2017-02-25 12:30:45 +00:00
<capacity unit= "LBS" > 412 </capacity> <!-- 1 percent of total fuel capacity, needs 20C -->
2016-12-07 18:05:28 +00:00
<contents unit= "LBS" > 0 </contents>
<priority > 4</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
</propulsion>
<system file= "pushback" />
<!-- system file="a320 - fuel" / -->
2017-04-17 04:10:36 +00:00
<system file= "glass-effect1" />
<system file= "it-fbw" />
2016-12-07 18:05:28 +00:00
<flight_control name= "FCS: A320" >
<channel name= "Pitch" >
<summer name= "Pitch Trim Sum" >
2017-05-03 02:16:53 +00:00
<input > /controls/flight/elevator-sum</input>
2016-12-07 18:05:28 +00:00
<input > /controls/flight/elevator-trim</input>
<clipto >
2017-04-07 18:09:40 +00:00
<min > -1</min>
<max > 1</max>
2016-12-07 18:05:28 +00:00
</clipto>
</summer>
<aerosurface_scale name= "Elevator Control" >
<input > fcs/pitch-trim-sum</input>
2017-04-07 18:09:40 +00:00
<gain > 0.015</gain>
2016-12-07 18:05:28 +00:00
<range >
2017-04-07 18:09:40 +00:00
<min > -20</min>
<max > 20</max>
2016-12-07 18:05:28 +00:00
</range>
<output > fcs/elevator-pos-rad</output>
</aerosurface_scale>
2017-04-07 18:09:40 +00:00
<aerosurface_scale name= "Elevator Position Normalizer" >
<input > fcs/pitch-trim-sum</input>
2016-12-07 18:05:28 +00:00
<range >
2017-04-07 18:09:40 +00:00
<min > -1</min>
<max > 1</max>
2016-12-07 18:05:28 +00:00
</range>
<output > fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name= "Roll" >
<summer name= "Roll Trim Sum" >
2017-05-03 02:16:53 +00:00
<input > /controls/flight/aileron-sum</input>
2016-12-07 18:05:28 +00:00
<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>
2017-05-07 19:26:41 +00:00
2016-12-07 18:05:28 +00:00
<channel name= "Yaw" >
2017-05-07 19:26:41 +00:00
<pure_gain name= "fcs/rudder-cmd" >
<input > /controls/flight/rudder-fdm</input>
<gain > -1</gain>
<output > fcs/rudder-cmd-norm</output>
2016-12-07 18:05:28 +00:00
</pure_gain>
2017-05-07 19:26:41 +00:00
2016-12-07 18:05:28 +00:00
<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>
2017-05-04 00:21:04 +00:00
<channel name= "Flaps" >
2016-12-07 18:05:28 +00:00
<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>
2017-05-04 00:21:04 +00:00
<time > 30</time>
2016-12-07 18:05:28 +00:00
</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>
2017-05-03 18:02:54 +00:00
<time > 1</time>
2016-12-07 18:05:28 +00:00
</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 >
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-0.20 -0.900
0.00 0.103
0.15 1.600
0.23 1.900
2017-05-07 19:26:41 +00:00
0.60 1.000
2016-12-07 18:05:28 +00:00
</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>
2017-05-07 19:26:41 +00:00
<table >
<independentVar lookup= "row" > fcs/flap-pos-norm</independentVar>
<tableData >
0.000 0.00000
2017-05-11 14:19:32 +00:00
0.290 0.00250
2017-05-07 19:26:41 +00:00
0.596 0.00700
0.645 0.01300
1.000 0.01700
</tableData>
</table>
2016-12-07 18:05:28 +00:00
</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>
2017-05-07 19:26:41 +00:00
<value > 0.01000 </value>
2016-12-07 18:05:28 +00:00
</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>
2017-05-07 19:26:41 +00:00
<value > -0.15</value>
2016-12-07 18:05:28 +00:00
</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>
2017-04-07 18:09:40 +00:00
<value > 0.04</value>
2016-12-07 18:05:28 +00:00
</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
2017-05-07 19:26:41 +00:00
0.26 0.028
1.57 1.350
2016-12-07 18:05:28 +00:00
</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>
2017-05-07 19:26:41 +00:00
<value > 0.00200 </value>
2016-12-07 18:05:28 +00:00
</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>
2017-05-07 19:26:41 +00:00
<value > 0.030</value>
2016-12-07 18:05:28 +00:00
</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>
2017-05-07 19:26:41 +00:00
<value > 0.03</value>
2016-12-07 18:05:28 +00:00
</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>
2017-04-07 18:09:40 +00:00
<value > -0.95</value>
2016-12-07 18:05:28 +00:00
</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>
2017-04-07 18:09:40 +00:00
<value > 0.005</value>
2016-12-07 18:05:28 +00:00
</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>
2017-04-07 18:09:40 +00:00
<value > 0.20</value>
2016-12-07 18:05:28 +00:00
</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>
2017-04-07 18:09:40 +00:00
<value > 0.003</value>
2016-12-07 18:05:28 +00:00
</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 >
2017-04-07 18:09:40 +00:00
0.0 -1.900
2.0 -0.900
2016-12-07 18:05:28 +00:00
</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>
2017-04-07 18:09:40 +00:00
<value > -140</value>
2016-12-07 18:05:28 +00:00
</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>
2017-04-07 18:09:40 +00:00
<value > -1</value>
2016-12-07 18:05:28 +00:00
</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>
2017-05-07 19:26:41 +00:00
<value > -0.2</value>
2016-12-07 18:05:28 +00:00
</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>
2017-05-07 19:26:41 +00:00
<value > -0.2</value>
2016-12-07 18:05:28 +00:00
</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>
