<?xml version="1.0"?> <?xml-stylesheet href="http://jsbsim.sourceforge.net/JSBSim.xsl" type="text/xsl"?> <fdm_config name="rascal" version="2.0" release="BETA" xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd"> <fileheader> <author> Author Name </author> <filecreationdate> Creation Date </filecreationdate> <version> Version </version> <description> Models a rascal </description> </fileheader> <metrics> <wingarea unit="FT2"> 10.57 </wingarea> <wingspan unit="FT"> 9.17 </wingspan> <chord unit="FT"> 1.15 </chord> <htailarea unit="FT2"> 1.69 </htailarea> <htailarm unit="FT"> 3.28 </htailarm> <vtailarea unit="FT2"> 1.06 </vtailarea> <vtailarm unit="FT"> 0 </vtailarm> <location name="AERORP" unit="IN"> <x> 37.4 </x> <y> 0 </y> <z> 0 </z> </location> <location name="EYEPOINT" unit="IN"> <x> 20 </x> <y> 0 </y> <z> 5 </z> </location> <location name="VRP" unit="IN"> <x> 0 </x> <y> 0 </y> <z> 0 </z> </location> </metrics> <mass_balance> <ixx unit="SLUG*FT2"> 1.95 </ixx> <iyy unit="SLUG*FT2"> 1.55 </iyy> <izz unit="SLUG*FT2"> 1.91 </izz> <ixy unit="SLUG*FT2"> 0 </ixy> <ixz unit="SLUG*FT2"> 0 </ixz> <iyz unit="SLUG*FT2"> 0 </iyz> <emptywt unit="LBS"> 13 </emptywt> <location name="CG" unit="IN"> <x> 36.4 </x> <y> 0 </y> <z> 4 </z> </location> </mass_balance> <ground_reactions> <contact type="BOGEY" name="LEFT_MLG"> <location unit="IN"> <x> 33.1 </x> <y> -12.9 </y> <z> -13.1 </z> </location> <static_friction> 0.8 </static_friction> <dynamic_friction> 0.5 </dynamic_friction> <rolling_friction> 0.1 </rolling_friction> <spring_coeff unit="LBS/FT"> 480 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 100 </damping_coeff> <max_steer unit="DEG"> 0.0 </max_steer> <brake_group> NONE </brake_group> <retractable>0</retractable> </contact> <contact type="BOGEY" name="RIGHT_MLG"> <location unit="IN"> <x> 33.1 </x> <y> 12.9 </y> <z> -13.1 </z> </location> <static_friction> 0.8 </static_friction> <dynamic_friction> 0.5 </dynamic_friction> <rolling_friction> 0.1 </rolling_friction> <spring_coeff unit="LBS/FT"> 480 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 100 </damping_coeff> <max_steer unit="DEG"> 0.0 </max_steer> <brake_group> NONE </brake_group> <retractable>0</retractable> </contact> <contact type="BOGEY" name="TAIL_LG"> <location unit="IN"> <x> 68.9 </x> <y> 0 </y> <z> -4 </z> </location> <static_friction> 0.8 </static_friction> <dynamic_friction> 0.5 </dynamic_friction> <rolling_friction> 0.1 </rolling_friction> <spring_coeff unit="LBS/FT"> 480 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 100 </damping_coeff> <max_steer unit="DEG"> 360.0 </max_steer> <brake_group> NONE </brake_group> <retractable>0</retractable> </contact> </ground_reactions> <propulsion> <engine file="Zenoah_G-26A"> <location unit="IN"> <x> 36 </x> <y> 0 </y> <z> 0 </z> </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0 </pitch> <yaw> 0 </yaw> </orient> <feed>0</feed> <thruster file="18x8"> <location unit="IN"> <x> 1 </x> <y> 0 </y> <z> 0 </z> </location> <orient unit="DEG"> <roll> 0.0 </roll> <pitch> 0.0 </pitch> <yaw> 0.0 </yaw> </orient> <p_factor>1.0</p_factor> </thruster> </engine> <tank type="FUEL"> <!-- Tank number 0 --> <location unit="IN"> <x> 36.36 </x> <y> 0 </y> <z> -1.89375 </z> </location> <capacity unit="LBS"> 1.5 </capacity> <contents unit="LBS"> 1.5 </contents> </tank> </propulsion> <flight_control name="FCS: rascal"> <channel name="All"> <summer name="Pitch Trim Sum"> <input>fcs/elevator-cmd-norm</input> <input>fcs/pitch-trim-cmd-norm</input> <clipto> <min>-1</min> <max>1</max> </clipto> </summer> <aerosurface_scale name="Elevator Control"> <input>fcs/pitch-trim-sum</input> <range> <min>-0.35</min> <max>0.3</max> </range> <output>fcs/elevator-pos-rad</output> </aerosurface_scale> <aerosurface_scale name="Elevator Normalized"> <input>fcs/elevator-pos-rad</input> <domain> <min>-0.3</min> <max> 0.3</max> </domain> <range> <min>-1</min> <max> 1</max> </range> <output>fcs/elevator-pos-norm</output> </aerosurface_scale> <summer name="Roll Trim Sum"> <input>fcs/aileron-cmd-norm</input> <input>fcs/roll-trim-cmd-norm</input> <clipto> <min>-1</min> <max>1</max> </clipto> </summer> <aerosurface_scale name="Left Aileron Control"> <input>fcs/roll-trim-sum</input> <range> <min>-0.35</min> <max>0.35</max> </range> <output>fcs/left-aileron-pos-rad</output> </aerosurface_scale> <aerosurface_scale name="Right Aileron Control"> <input>-fcs/roll-trim-sum</input> <range> <min>-0.35</min> <max>0.35</max> </range> <output>fcs/right-aileron-pos-rad</output> </aerosurface_scale> <aerosurface_scale name="Left aileron Normalized"> <input>fcs/left-aileron-pos-rad</input> <domain> <min>-0.35</min> <max> 0.35</max> </domain> <range> <min>-1</min> <max> 1</max> </range> <output>fcs/left-aileron-pos-norm</output> </aerosurface_scale> <aerosurface_scale name="Right aileron Normalized"> <input>fcs/right-aileron-pos-rad</input> <domain> <min>-0.35</min> <max> 0.35</max> </domain> <range> <min>-1</min> <max> 1</max> </range> <output>fcs/right-aileron-pos-norm</output> </aerosurface_scale> <summer name="Rudder Command Sum"> <input>fcs/rudder-cmd-norm</input> <input>fcs/yaw-trim-cmd-norm</input> <clipto> <min>-1</min> <max>1</max> </clipto> </summer> <aerosurface_scale name="Rudder Control"> <input>fcs/rudder-command-sum</input> <range> <min>-0.35</min> <max>0.35</max> </range> <output>fcs/rudder-pos-rad</output> </aerosurface_scale> <aerosurface_scale name="Rudder Normalized"> <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> </flight_control> <aerodynamics> <axis name="DRAG"> <function name="aero/coefficient/CD0"> <description>Drag_at_zero_lift</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <table> <independentVar>aero/alpha-rad</independentVar> <tableData> -1.5700 1.5000 -0.2600 0.0560 0.0000 0.0280 0.2600 0.0560 1.5700 1.5000 </tableData> </table> </product> </function> <function name="aero/coefficient/CDi"> <description>Induced_drag</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>aero/cl-squared</property> <value>0.0400</value> </product> </function> <function name="aero/coefficient/CDbeta"> <description>Drag_due_to_sideslip</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <table> <independentVar>aero/beta-rad</independentVar> <tableData> -1.5700 1.2300 -0.2600 0.0500 0.0000 0.0000 0.2600 0.0500 1.5700 1.2300 </tableData> </table> </product> </function> <function name="aero/coefficient/CDde"> <description>Drag_due_to_Elevator_Deflection</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>fcs/elevator-pos-norm</property> <value>0.0300</value> </product> </function> </axis> <axis name="SIDE"> <function name="aero/coefficient/CYb"> <description>Side_force_due_to_beta</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>aero/beta-rad</property> <value>-1.0000</value> </product> </function> </axis> <axis name="LIFT"> <function name="aero/coefficient/CLalpha"> <description>Lift_due_to_alpha</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <table> <independentVar>aero/alpha-rad</independentVar> <tableData> -0.2000 -0.7500 0.0000 0.2500 0.2300 1.4000 0.6000 0.7100 </tableData> </table> </product> </function> <function name="aero/coefficient/CLde"> <description>Lift_due_to_Elevator_Deflection</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>fcs/elevator-pos-rad</property> <value>0.2000</value> </product> </function> </axis> <axis name="ROLL"> <function name="aero/coefficient/Clb"> <description>Roll_moment_due_to_beta</description> <!-- aka dihedral effect --> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <property>aero/beta-rad</property> <value>-0.1000</value> </product> </function> <function name="aero/coefficient/Clp"> <description>Roll_moment_due_to_roll_rate</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <property>aero/bi2vel</property> <property>velocities/p-aero-rad_sec</property> <value>-0.4000</value> </product> </function> <function name="aero/coefficient/Clr"> <description>Roll_moment_due_to_yaw_rate</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <property>aero/bi2vel</property> <property>velocities/r-aero-rad_sec</property> <value>0.1500</value> </product> </function> <function name="aero/coefficient/Clda"> <description>Roll_moment_due_to_aileron</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <property>fcs/left-aileron-pos-rad</property> <table> <independentVar>velocities/mach</independentVar> <tableData> 0.0000 0.1300 2.0000 0.0570 </tableData> </table> </product> </function> <function name="aero/coefficient/Cldr"> <description>Roll_moment_due_to_rudder</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <property>fcs/rudder-pos-rad</property> <value>0.0100</value> </product> </function> </axis> <axis name="PITCH"> <function name="aero/coefficient/Cmalpha"> <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>-0.5000</value> </product> </function> <function name="aero/coefficient/Cmde"> <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>velocities/mach</independentVar> <tableData> 0.0000 -0.5000 <!-- was -1.1 --> 2.0000 -0.2750 </tableData> </table> </product> </function> <function name="aero/coefficient/Cmq"> <description>Pitch_moment_due_to_pitch_rate</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/cbarw-ft</property> <property>aero/ci2vel</property> <property>velocities/q-aero-rad_sec</property> <value>-12.0000</value> </product> </function> <function name="aero/coefficient/Cmadot"> <description>Pitch_moment_due_to_alpha_rate</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/cbarw-ft</property> <property>aero/ci2vel</property> <property>aero/alphadot-rad_sec</property> <value>-7.0000</value> </product> </function> </axis> <axis name="YAW"> <function name="aero/coefficient/Cnb"> <description>Yaw_moment_due_to_beta</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <property>aero/beta-rad</property> <value>0.1200</value> </product> </function> <function name="aero/coefficient/Cnr"> <description>Yaw_moment_due_to_yaw_rate</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <property>aero/bi2vel</property> <property>velocities/r-aero-rad_sec</property> <value>-0.1500</value> </product> </function> <function name="aero/coefficient/Cndr"> <description>Yaw_moment_due_to_rudder</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <property>fcs/rudder-pos-rad</property> <value>-0.0500</value> </product> </function> <function name="aero/coefficient/Cnda"> <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>-0.0300</value> </product> </function> <function name="aero/coefficient/Cndi"> <description>Yaw_moment_due_to_tail_incidence</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/bw-ft</property> <value>0.0007</value> </product> </function> </axis> </aerodynamics> <!-- <output name="RascalOutputFile.csv" type="CSV" rate="10"> <rates> ON </rates> <velocities> ON </velocities> <position> ON </position> <fcs> ON </fcs> <propulsion> ON </propulsion> </output> --> <input port="5505"/> </fdm_config>