<?xml version="1.0"?> <?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 A321-231 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"> <x> 700.00 </x> <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"> <x> 652.00 </x> <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="v2533_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="v2533_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><!-- 1 percent of total capacity, needs 20C to be filled --> <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><!-- correct by FCOM --> <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 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><!-- need review --> <contents unit="LBS"> 1520 </contents><!-- outer tank filled first than inner tank --> <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><!-- 1 percent of total fuel capacity, needs 20C--> <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>