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From: Erik H. <eh...@us...> - 2015-10-29 13:14:31
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Update of /cvsroot/jsbsim/JSBSim/aircraft/Pterosaur In directory sfp-cvs-1.v30.ch3.sourceforge.com:/tmp/cvs-serv27406/aircraft/Pterosaur Added Files: Pterosaur.xml Log Message: Add a engineless model of a Pterosaur that uses whing motion to geenrate lift and thrust --- NEW FILE --- <?xml version="1.0"?> <?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?> <fdm_config name="Pterosaur" version="2.0" release="ALPHA" xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd"> <fileheader> <author> Aeromatic v 2.9.9 </author> <filecreationdate> 27 Oct 2015 </filecreationdate> <version>$Revision: 1.1 $</version> <description> Models a Pterosaur. </description> </fileheader> <!-- File: Pterosaur.xml Inputs: name: Pterosaur type: glider max weight: 352.02 lb wing span: 36.75 ft length: 32.81 ft wing area: 47.36 sq-ft gear type: taildragger steering type: steering retractable?: yes Outputs: wing loading: 9.54 lb/sq-ft payload: 104.87 lbs CL-alpha: 5.50 per radian CL-0: 0.25 CL-max: 1.40 CD-0: 0.01 K: 0.02 References: * "Flight in slow motion: aerodynamics of the pterosaur wing" http://rspb.royalsocietypublishing.org/content/278/1713/1881.full.pdf * "Student guest blog post: pterosaur weight estimation" http://lorenabarba.com/blog/student-guest-blog-post-pterosaur-weight-estimation/ * "Pterosaur flight" http://www.transitionrig.com/pterosau.htm "These animals were capable of active, flapping flight, accelerating from launch to cruise in approximately 15-20 wing strokes. The two animals both had a very high aspect ratio and did not connect the flight membrane (patagium) to the leg (which carried its own uropatagium and together with the tiny biological tail, formed an aerodynamic tail structure). When soaring, they both had an L/D max on the rough order of 28:1 (about equal to the Carbon Dragon and the WinDancer, and in the case of Qn a a similar gross weight), and actively modified their wing planform in a manner somewhat similar to birds, but controlled sail camber, chord, and planform in the outer wing membrane with fine structures called aktinofibrils which were generally oriented more diagonally than sail battens. The aktinofibrils worked in diagonal tension, maintaining a camber somewhat similar to Selig's S1223, but with a thinner airfoil section (outboard, that is - inboard at the elbow (which for Qn measured 10.5 inches from top to bottom, T/C max was about 32% and the aktinofibril orientation was more amorphous). Throughout the wing, zero lift occurred at about -8 to -10.5 degrees, with a quarter chord pitching moment about -0.3." * "The principle of flight of ornithopters" http://www.ornithopter.de/english/principle.htm --> <metrics> <wingarea unit="FT2"> 47.36 </wingarea> <wingspan unit="FT" > 36.75 </wingspan> <wing_incidence> 2.00 </wing_incidence> <chord unit="FT" > 1.29 </chord> <htailarea unit="FT2"> 63.70 </htailarea> <htailarm unit="FT" > 16.46 </htailarm> <vtailarea unit="FT2"> 4.74 </vtailarea> <vtailarm unit="FT" > 16.41 </vtailarm> <location name="AERORP" unit="IN"> <x> 188.99 </x> <y> 0.00 </y> <z> 0.00 </z> </location> <location name="EYEPOINT" unit="IN"> <x> 51.18 </x> <y> -18.00 </y> <z> 45.00 </z> </location> <location name="VRP" unit="IN"> <x> 0.0 </x> <y> 0.0 </y> <z> 0.0 </z> </location> </metrics> <mass_balance> <ixx unit="SLUG*FT2"> 166.83 </ixx> <iyy unit="SLUG*FT2"> 242.14 </iyy> <izz unit="SLUG*FT2"> 361.58 </izz> <emptywt unit="LBS" > 187.26 </emptywt> <location name="CG" unit="IN"> <x> 188.99 </x> <y> 0.00 </y> <z> -9.84 </z> </location> </mass_balance> <propulsion> <engine file="dummy"> <location unit="IN"> <x> 36.00 </x> <y> 0.00 </y> <z> 0.00 </z> </location> <orient unit="DEG"> <pitch> 0.00 </pitch> <roll> 0.00 </roll> <yaw> 0.00 </yaw> </orient> <feed> 0 </feed> <thruster file="direct"> <sense> 1 </sense> <location unit="IN"> <x> 36.00 </x> <y> 0.00 </y> <z> 0.00 </z> </location> <orient unit="DEG"> <pitch> 0.00 </pitch> <roll> 0.00 </roll> <yaw> 0.00 </yaw> </orient> </thruster> </engine> </propulsion> <ground_reactions> <contact type="BOGEY" name="TAIL"> <location unit="IN"> <x> 253.18 </x> <y> 0.00 </y> <z> -65.62 </z> </location> <static_friction> 0.80 </static_friction> <dynamic_friction> 0.05 </dynamic_friction> <rolling_friction> 0.001 </rolling_friction> <spring_coeff unit="LBS/FT"> 352 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 176 </damping_coeff> <max_steer unit="DEG"> 0.50 </max_steer> <brake_group> NONE </brake_group> <retractable> 1 </retractable> </contact> <contact type="BOGEY" name="LEFT_MAIN"> <location unit="IN"> <x> 171.98 </x> <y> -39.69 </y> <z> -78.74 </z> </location> <static_friction> 0.80 </static_friction> <dynamic_friction> 0.05 </dynamic_friction> <rolling_friction> 0.001 </rolling_friction> <spring_coeff unit="LBS/FT"> 352 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 176 </damping_coeff> <max_steer unit="DEG">0</max_steer> <brake_group> LEFT </brake_group> <retractable> 1 </retractable> </contact> <contact type="BOGEY" name="RIGHT_MAIN"> <location unit="IN"> <x> 171.98 </x> <y> 39.69 </y> <z> -78.74 </z> </location> <static_friction> 0.80 </static_friction> <dynamic_friction> 0.05 </dynamic_friction> <rolling_friction> 0.001 </rolling_friction> <spring_coeff unit="LBS/FT"> 352 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 176 </damping_coeff> <max_steer unit="DEG">0</max_steer> <brake_group> RIGHT </brake_group> <retractable> 1 </retractable> </contact> <!-- <contact type="STRUCTURE" name="BELLY"> <location unit="IN"> <x> 0.00 </x> <y> 0.00 </y> <z> -9.84 </z> </location> <static_friction> 0.3 </static_friction> <dynamic_friction> 0.2 </dynamic_friction> <spring_coeff unit="LBS/FT"> 5500 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 550 </damping_coeff> </contact> --> <contact type="STRUCTURE" name="LEFT_WING"> <location unit="IN"> <x> 188.99 </x> <y> -18.38 </y> <z> -9.84 </z> </location> <static_friction> 1 </static_friction> <dynamic_friction> 1 </dynamic_friction> <spring_coeff unit="LBS/FT"> 352 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 352 </damping_coeff> </contact> <contact type="STRUCTURE" name="RIGHT_WING"> <location unit="IN"> <x> 188.99 </x> <y> 18.38 </y> <z> -9.84 </z> </location> <static_friction> 1 </static_friction> <dynamic_friction> 1 </dynamic_friction> <spring_coeff unit="LBS/FT"> 352 </spring_coeff> <damping_coeff unit="LBS/FT/SEC"> 352 </damping_coeff> </contact> </ground_reactions> <system file="Ornithopter Controls.xml"/> <system file="Landing Gear.xml"/> <system file="Wing Motion.xml"/> <flight_control name="FCS: Pterosaur"> </flight_control> <aerodynamics> <function name="aero/function/kCLge"> <description>Change_in_lift_due_to_ground_effect</description> <product> <table> <independentVar>aero/h_b-mac-ft</independentVar> <tableData> 0.0000 1.3910 0.1000 1.2350 0.1500 1.1670 0.2000 1.1350 0.3000 1.0850 0.4000 1.1020 0.5000 1.0350 0.6000 1.0240 0.7000 1.0150 0.8000 1.0110 0.9000 1.0060 1.0000 1.0040 1.1000 1.0000 </tableData> </table> </product> </function> <axis name="LIFT"> <function name="aero/force/Lift_alpha"> <description>Lift due to alpha of the body</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <table> <independentVar lookup="row">aero/alpha-deg</independentVar> <tableData> -12.0 -0.750 0.00 0.250 12.0 1.400 35.0 0.710 </tableData> </table> </product> </function> <function name="aero/force/Lift_wing_incidence"> <description>Lift due to alpha of the wings</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <table> <independentVar lookup="row">fcs/wing-alpha-deg</independentVar> <tableData> -15.0 0.0 -10.0 0.4 -5.0 1.0 0.0 1.5 5.0 2.0 10.0 1.9 15.0 1.5 20.0 1.0 </tableData> </table> </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> 0.0800 </value> </product> </function> </axis> <axis name="DRAG"> <function name="aero/force/Drag_wing_incidence"> <description>Delta Drag due to wing angle</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <table> <independentVar lookup="row">fcs/wing-alpha-deg</independentVar> <tableData> -30.0 -0.800 -25.0 -0.450 -20.0 -0.275 -15.0 -0.080 -10.0 -0.050 -5.0 -0.030 0.0 0.000 5.0 0.000 10.0 0.001 15.0 0.009 20.0 0.011 25.0 0.013 30.0 0.020 </tableData> </table> </product> </function> <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-deg</independentVar> <tableData> -90.0 1.5000 -60.0 0.0110 0.0 0.0090 60.0 0.0110 90.0 1.5000 </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> 0.0095 </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-deg</independentVar> <tableData> -90.0 1.2300 -15.0 0.0500 0.00 0.0000 15.0 0.0500 90.0 1.2300 </tableData> </table> </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> 0.1110 </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> -1.0000 </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> -0.2500 </value> </product> </function> <function name="aero/moment/Pitch_wing_incidence"> <description>Pitch due to alpha of the wings</description> <product> <property>aero/qbar-psf</property> <property>metrics/Sw-sqft</property> <property>metrics/cbarw-ft</property> <table> <independentVar lookup="row">fcs/wing-alpha-deg</independentVar> <tableData> -5.0 0.0 0.0 -0.0251 5.0 -0.0628 10.0 -0.0942 15.0 -0.1256 20.0 -0.1193 25.0 -0.0942 30.0 -0.0628 </tableData> </table> </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> <value> -0.8000 </value> </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> -12.0000 </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> -9.0000 </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> -0.1000 </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> -0.4000 </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> 0.1500 </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> 0.0700 </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> 0.1200 </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> -0.1500 </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> -0.0100 </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>-0.019</value> </product> </function> </axis> </aerodynamics> <external_reactions> </external_reactions> </fdm_config> |