677 lines
20 KiB
XML
677 lines
20 KiB
XML
<FDM_CONFIG NAME="c172" VERSION="1.65">
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<!--
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File: c172p.xml
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Author: David Megginson (based on c172r.xml by Tony Peden)
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CVS Version: $Id$
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Function: Models a 1981 Cessna 172P.
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Sources:
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Tony Peden, c172r.xml, JSBSim (http://jsbsim.sourceforge.net/).
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Jan Roskam, Airplane Flight Dynamics and Automatic Flight
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Controls. Part I. DARcorporation, 1995.
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Notes:
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Roskam's data is for a 182, not a 172, but it should be close
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enough. He gives linear coefficients for three states:
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1. Climb (5.4 deg alpha).
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2. Cruise (0 deg alpha).
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3. Approach (4 deg alpha, and presumably, full flaps).
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I have extrapolated small tables from this data to account for the
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effects of flaps and alpha, especially in the lateral coefficients.
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-->
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<METRICS>
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<!--
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// Wing area (ft^2)
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// Wing span (ft)
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// Wing avg. chord (ft)
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// H. Tail Area (ft^2)
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// Wing MAC to H.Tail MAC (ft)
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// V. Tail Area (ft^2)
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// Wing MAC to V.Tail MAC (ft)
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// Ixx
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// Iyy
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// Izz
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// Ixz
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// Empty weight
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// Center of gravity location, empty weight, in aircraft's own structural coord
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// system. X, Y, Z, in inches
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// Pilot's eyepoint location, in aircraft's own coord system, FROM cg.
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// X, Y, Z, in inches
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AC_AERORP 43.2 0.0 59.4
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-->
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AC_WINGAREA 174 <!-- square feet -->
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AC_WINGSPAN 35.8 <!-- ft -->
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AC_CHORD 4.9 <!-- ft -->
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AC_HTAILAREA 21.9 <!-- square feet -->
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AC_HTAILARM 15.7 <!-- ft -->
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AC_VTAILAREA 16.5 <!-- square feet -->
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AC_LV 15.7 <!-- ft -->
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AC_IXX 948
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AC_IYY 1346
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AC_IZZ 1967
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AC_IXZ 0
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AC_EMPTYWT 1500
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AC_AERORP 43.2 0.0 59.4
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AC_CGLOC 41.0 0.0 36.5
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<!-- Pilot -->
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AC_POINTMASS 180.0 36.0 -14.0 24.0
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<!-- Co-pilot -->
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<!-- AC_POINTMASS 180.0 36.0 14.0 24.0 -->
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AC_EYEPTLOC 37.0 0.0 48.0
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AC_VRP 42.6 0.0 38.5
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</METRICS>
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<UNDERCARRIAGE>
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<!--
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The gear parameters that can be specified are as follows, IN ORDER OF APPEARANCE:
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AC_GEAR
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<name> name of gear entry - no spaces allowed
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<X> <Y> <Z> Gear location in aircraft body coords in inches
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<spring constant> spring constant in lbs/ft
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<damping coefficient> damping coefficient in lbs/ft/sec
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<dynamic friction coefficient> Self-explanatory: sliding friction coefficient
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<static friction coefficient> Self-explanatory: "onset" friction coefficient
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<rolling friction coefficient> Self-explanatory: rolling friction coefficient
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<steerability attribute> One of <STEERABLE | FIXED | CASTERED>
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<brake group membership> One of <LEFT | CENTER | RIGHT | NOSE | TAIL | NONE>
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<max steer angle> Maximum steerable angle in degrees
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<retraction attribute> <RETRACT | FIXED>
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-->
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AC_GEAR NOSE -6.8 0.0 -20.0 1800 600 0.5 0.8 0.02 STEERABLE NONE 10 FIXED
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AC_GEAR LEFT_MAIN 58.2 -43.0 -17.9 5400 1600 0.5 0.8 0.02 FIXED LEFT 0 FIXED
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AC_GEAR RIGHT_MAIN 58.2 43.0 -17.9 5400 1600 0.5 0.8 0.02 FIXED RIGHT 0 FIXED
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AC_GEAR TAIL_SKID 188.0 0.0 8.0 20000 1000 0.2 0.2 0.2 FIXED NONE 0 FIXED
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AC_GEAR LEFT_TIP 43.2 -214.8 59.4 10000 2000 0.2 0.2 0.2 FIXED NONE 0 FIXED
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AC_GEAR RIGHT_TIP 43.2 214.8 59.4 10000 2000 0.2 0.2 0.2 FIXED NONE 0 FIXED
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</UNDERCARRIAGE>
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<PROPULSION>
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<!--
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TANKS SECTION
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Tank locations and characteristics, empty weight, in aircraft's own coord system:
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X, Y, Z, in inches
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effective radius of tank, in inches (for fuel slosh, if/when modeled)
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capacity in pounds
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Current contents, in pounds
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ENGINE[S] SECTION
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Engine[s] is|are specified by giving engine name (which corresponds to an engine
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definition file in the "engines" directory) followed by x, y, z placement and
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pitch and yaw orientation. Coordinates are given in inches in the structural
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coordinate frame. Angles for pitch and yaw are specified in radians.
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AC_ENGINE name x y z pitch yaw
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THRUSTER[S] SECTION
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AC_THRUSTER name x y z pitch yaw
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-->
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<AC_ENGINE FILE="eng_io320">
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XLOC -19.7
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YLOC 0.0
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ZLOC 26.6
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PITCH 0.0
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YAW 0.0
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FEED 0
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FEED 1
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<AC_THRUSTER FILE="prop_75in2f">
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XLOC -37.7
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YLOC 0.0
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ZLOC 26.6
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PITCH 0.0
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YAW 0
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P_FACTOR 10.0
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SENSE 1.0
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</AC_THRUSTER>
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</AC_ENGINE>
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<AC_TANK TYPE="FUEL" NUMBER="0">
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XLOC 56.0
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YLOC -112.0
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ZLOC 59.4
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RADIUS 29.4
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CAPACITY 185.0
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CONTENTS 100.0
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</AC_TANK>
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<AC_TANK TYPE="FUEL" NUMBER="1">
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XLOC 56.0
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YLOC 112.0
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ZLOC 59.4
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RADIUS 29.4
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CAPACITY 185.0
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CONTENTS 100.0
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</AC_TANK>
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</PROPULSION>
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<FLIGHT_CONTROL NAME="c172">
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<COMPONENT NAME="Pitch Trim Sum" TYPE="SUMMER">
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INPUT fcs/elevator-cmd-norm
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INPUT fcs/pitch-trim-cmd-norm
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CLIPTO -1 1
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</COMPONENT>
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<COMPONENT NAME="Elevator Control" TYPE="AEROSURFACE_SCALE">
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INPUT fcs/pitch-trim-sum
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MIN -28
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MAX 23
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OUTPUT fcs/elevator-pos-rad
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GAIN 0.01745
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</COMPONENT>
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<COMPONENT NAME="Roll Trim Sum" TYPE="SUMMER">
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INPUT fcs/aileron-cmd-norm
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INPUT fcs/roll-trim-cmd-norm
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CLIPTO -1 1
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</COMPONENT>
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<COMPONENT NAME="Left Aileron Control" TYPE="AEROSURFACE_SCALE">
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INPUT fcs/roll-trim-sum
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MIN -20
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MAX 15
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GAIN 0.01745
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OUTPUT fcs/left-aileron-pos-rad
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</COMPONENT>
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<COMPONENT NAME="Right Aileron Control" TYPE="AEROSURFACE_SCALE">
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INPUT fcs/roll-trim-sum
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MIN -20
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MAX 15
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GAIN -0.01745
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OUTPUT fcs/right-aileron-pos-rad
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</COMPONENT>
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<COMPONENT NAME="Yaw Trim Sum" TYPE="SUMMER">
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INPUT fcs/rudder-cmd-norm
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INPUT fcs/yaw-trim-cmd-norm
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CLIPTO -1 1
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</COMPONENT>
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<COMPONENT NAME="Rudder Control" TYPE="AEROSURFACE_SCALE">
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INPUT fcs/yaw-trim-sum
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MIN -16
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MAX 16
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GAIN 0.01745
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OUTPUT fcs/rudder-pos-rad
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</COMPONENT>
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<COMPONENT NAME="Flaps Control" TYPE="KINEMAT">
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INPUT fcs/flap-cmd-norm
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DETENTS 4
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0 0
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10 2
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20 1
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30 1
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OUTPUT fcs/flap-pos-deg
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</COMPONENT>
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</FLIGHT_CONTROL>
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<AERODYNAMICS>
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AC_ALPHALIMITS -0.087 0.28
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AC_HYSTLIMITS 0.09 0.36
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<AXIS NAME="LIFT">
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<GROUP NAME="CLb">
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Basic_lift
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<!-- Peden -->
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<FACTOR NAME="kCLge" TYPE="VECTOR">
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Change_in_lift_due_to_ground_effect
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13
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aero/h_b-mac-ft
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none
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0.0 1.203
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0.1 1.127
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0.15 1.090
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0.2 1.073
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0.3 1.046
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0.4 1.055
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0.5 1.019
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0.6 1.013
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0.7 1.008
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0.8 1.006
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0.9 1.003
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1.0 1.002
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1.1 1.0
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</FACTOR>
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<!-- Peden -->
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<COEFFICIENT NAME="CLwbh" TYPE="TABLE">
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Lift_due_to_alpha
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17
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2
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aero/alpha-rad
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aero/stall-hyst-norm
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aero/qbar-psf | metrics/Sw-sqft
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0 1
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-0.09 -0.22 -0.22
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0 0.25 0.25
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0.09 0.73 0.73
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0.1 0.83 0.78
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0.12 0.92 0.79
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0.14 1.02 0.81
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0.16 1.08 0.82
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0.17 1.13 0.83
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0.19 1.19 0.85
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0.21 1.25 0.86
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0.24 1.35 0.88
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0.26 1.44 0.9
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0.28 1.47 0.92
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0.3 1.43 0.95
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0.32 1.38 0.99
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0.34 1.3 1.05
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0.36 1.15 1.15
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</COEFFICIENT>
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<!-- Peden -->
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<COEFFICIENT NAME="CLDf" TYPE="VECTOR">
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Delta_lift_due_to_flap_deflection
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4
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fcs/flap-pos-deg
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aero/qbar-psf | metrics/Sw-sqft
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0 0
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10 0.20
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20 0.30
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30 0.35
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</COEFFICIENT>
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</GROUP>
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<!-- Roskam p.481 -->
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<COEFFICIENT NAME="CLDe" TYPE="VALUE">
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Lift_due_to_Elevator_Deflection
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aero/qbar-psf | metrics/Sw-sqft | fcs/elevator-pos-rad
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0.43
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</COEFFICIENT>
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<!-- Roskam p.481 -->
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<COEFFICIENT NAME="CLadot" TYPE="VALUE">
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Lift_due_to_alpha_rate
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aero/qbar-psf | metrics/Sw-sqft | aero/alphadot-rad_sec | aero/ci2vel
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1.7
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</COEFFICIENT>
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<!-- Roskam p.481 -->
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<COEFFICIENT NAME="CLq" TYPE="VALUE">
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Lift_due_to_pitch_rate
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aero/qbar-psf | metrics/Sw-sqft | velocities/q-aero-rad_sec | aero/ci2vel
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3.9
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</COEFFICIENT>
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</AXIS>
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<AXIS NAME="DRAG">
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<!-- Roskam p.481 -->
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<COEFFICIENT NAME="CDo" TYPE="VALUE">
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Drag_at_zero_lift
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aero/qbar-psf | metrics/Sw-sqft
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0.0270
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</COEFFICIENT>
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<GROUP NAME="CDb">
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Basic_drag
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<!-- Peden -->
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<FACTOR NAME="kCDge" TYPE="VECTOR">
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Change_in_drag_due_to_ground_effect
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13
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aero/h_b-mac-ft
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none
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0.0 0.048
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0.1 0.515
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0.15 0.629
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0.2 0.709
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0.3 0.815
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0.4 0.882
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0.5 0.928
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0.6 0.962
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0.7 0.988
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0.8 1.0
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0.9 1.0
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1.0 1.0
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1.1 1.0
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</FACTOR>
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<!-- Peden -->
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<COEFFICIENT NAME="CDDf" TYPE="VECTOR">
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Delta_drag_due_to_flap_deflection
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4
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fcs/flap-pos-deg
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aero/qbar-psf | metrics/Sw-sqft
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0 0
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10 0.007
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20 0.012
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30 0.018
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</COEFFICIENT>
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<!-- Peden -->
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<COEFFICIENT NAME="CDwbh" TYPE="TABLE">
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Drag_due_to_alpha
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26
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4
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aero/alpha-rad
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fcs/flap-pos-deg
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aero/qbar-psf | metrics/Sw-sqft
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0 10 20 30
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-0.0872664 0.00407143 3.8165e-05 0.000512444 0.00137231
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-0.0698132 0.0013424 0.000440634 0.00248067 0.00412341
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-0.0523599 8.96747e-05 0.00231942 0.0059252 0.00835082
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-0.0349066 0.000313268 0.00567451 0.0108461 0.0140545
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-0.0174533 0.00201318 0.0105059 0.0172432 0.0212346
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0 0.0051894 0.0168137 0.0251167 0.0298909
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0.0174533 0.00993967 0.0247521 0.0346492 0.0402205
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0.0349066 0.0162201 0.0342207 0.0457119 0.0520802
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0.0523599 0.0240308 0.0452195 0.0583047 0.0654701
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0.0698132 0.0333717 0.0577485 0.0724278 0.0803902
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0.0872664 0.0442427 0.0718077 0.088081 0.0968405
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0.10472 0.056644 0.0873971 0.105265 0.114821
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0.122173 0.0705754 0.104517 0.123978 0.134332
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0.139626 0.086037 0.123166 0.144222 0.155373
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0.15708 0.096239 0.135317 0.157346 0.168984
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0.174533 0.106859 0.147857 0.170848 0.182966
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0.191986 0.118034 0.160954 0.184905 0.197503
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0.209439 0.129765 0.174606 0.199517 0.212596
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0.226893 0.142366 0.189176 0.215072 0.228643
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0.244346 0.156452 0.205363 0.23231 0.246406
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0.261799 0.172732 0.223956 0.252059 0.266733
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0.279253 0.178209 0.230187 0.258667 0.273529
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0.296706 0.171598 0.222665 0.25069 0.265325
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0.314159 0.161786 0.211468 0.2388 0.253089
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0.331613 0.147493 0.19508 0.221364 0.235129
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0.349066 0.109678 0.151171 0.174408 0.186649
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</COEFFICIENT>
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</GROUP>
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<!-- Roskam p.481 -->
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<COEFFICIENT NAME="CDDe" TYPE="VALUE">
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Drag_due_to_Elevator_Deflection
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aero/qbar-psf | metrics/Sw-sqft | fcs/mag-elevator-pos-rad
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0
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</COEFFICIENT>
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<!-- Peden -->
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<COEFFICIENT NAME="CDbeta" TYPE="VALUE">
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Drag_due_to_sideslip
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aero/qbar-psf | metrics/Sw-sqft | aero/mag-beta-rad
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0.17
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</COEFFICIENT>
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</AXIS>
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<AXIS NAME="SIDE">
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<!-- based on Roskam p.482, clamped to +/-20deg beta -->
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<COEFFICIENT NAME="CYb" TYPE="TABLE">
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Side_force_due_to_beta
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3
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2
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aero/beta-rad
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fcs/flap-pos-deg
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aero/qbar-psf | metrics/Sw-sqft
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0 30
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-0.349 0.137 0.106
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0 0 0
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0.349 -0.137 -0.106
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</COEFFICIENT>
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<!-- Roskam p.482 -->
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<COEFFICIENT NAME="CYda" TYPE="VALUE">
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Side_force_due_to_aileron
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aero/qbar-psf | metrics/Sw-sqft | fcs/left-aileron-pos-rad
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0
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</COEFFICIENT>
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<!-- Roskam p.482 -->
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<COEFFICIENT NAME="CYdr" TYPE="VALUE">
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Side_force_due_to_rudder
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aero/qbar-psf | metrics/Sw-sqft | fcs/rudder-pos-rad
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0.187
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</COEFFICIENT>
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<!-- based on Roskam p.482 -->
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<COEFFICIENT NAME="CYp" TYPE="TABLE">
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Side_force_due_to_roll_rate
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2
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2
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aero/alpha-rad
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fcs/flap-pos-deg
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aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/p-aero-rad_sec
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0 30
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0.000 -0.075 -0.161
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0.094 -0.145 -0.231
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</COEFFICIENT>
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<!-- based on Roskam p.482 -->
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<COEFFICIENT NAME="CYr" TYPE="TABLE">
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Side_force_due_to_yaw_rate
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2
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2
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aero/alpha-rad
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fcs/flap-pos-deg
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aero/qbar-psf | metrics/Sw-sqft | aero/bi2vel | velocities/r-aero-rad_sec
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0 30
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0.000 0.214 0.162
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0.094 0.267 0.215
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</COEFFICIENT>
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</AXIS>
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<AXIS NAME="ROLL">
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<!-- based on Roskam p.482, clamped to +/-20deg beta -->
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<COEFFICIENT NAME="Clb" TYPE="VECTOR">
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Roll_moment_due_to_beta
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3
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aero/beta-rad
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aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
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-0.349 0.0322
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0 0
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0.349 -0.0322
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</COEFFICIENT>
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<!-- Roskam p.482 -->
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<COEFFICIENT NAME="Clp" TYPE="VALUE">
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Roll_moment_due_to_roll_rate_(roll_damping)
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aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
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-0.484
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</COEFFICIENT>
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<!-- based on Roskam p.482 -->
|
|
<COEFFICIENT NAME="Clr" TYPE="TABLE">
|
|
Roll_moment_due_to_yaw_rate
|
|
2
|
|
2
|
|
aero/alpha-rad
|
|
fcs/flap-pos-deg
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
|
|
0 30
|
|
0.000 0.0798 0.1246
|
|
0.094 0.1869 0.2317
|
|
</COEFFICIENT>
|
|
|
|
<!-- Roskam p.482 -->
|
|
<COEFFICIENT NAME="ClDa" TYPE="VALUE">
|
|
Roll_moment_due_to_aileron
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
|
|
0.229
|
|
</COEFFICIENT>
|
|
|
|
<!-- Roskam p.482 -->
|
|
<COEFFICIENT NAME="Cldr" TYPE="VALUE">
|
|
Roll_moment_due_to_rudder
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
|
|
0.0147
|
|
</COEFFICIENT>
|
|
|
|
</AXIS>
|
|
|
|
<AXIS NAME="PITCH">
|
|
|
|
<!-- Peden -->
|
|
<COEFFICIENT NAME="Cmo" TYPE="VALUE">
|
|
Pitching_moment_at_zero_alpha
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft
|
|
0.1
|
|
</COEFFICIENT>
|
|
|
|
<!-- Peden -->
|
|
<COEFFICIENT NAME="Cmalpha" TYPE="VALUE">
|
|
Pitch_moment_due_to_alpha
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/alpha-rad
|
|
-1.8
|
|
</COEFFICIENT>
|
|
|
|
<!-- Roskam p.481 -->
|
|
<COEFFICIENT NAME="Cmq" TYPE="VALUE">
|
|
Pitch_moment_due_to_pitch_rate
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | velocities/q-aero-rad_sec
|
|
-12.4
|
|
</COEFFICIENT>
|
|
|
|
<!-- based on Roskam p.481 -->
|
|
<COEFFICIENT NAME="Cmadot" TYPE="VALUE">
|
|
Pitch_moment_due_to_alpha_rate
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | aero/ci2vel | aero/alphadot-rad_sec
|
|
-7.27
|
|
</COEFFICIENT>
|
|
|
|
<!-- Roskam p.481 -->
|
|
<COEFFICIENT NAME="Cmde" TYPE="VALUE">
|
|
Pitch_moment_due_to_elevator_deflection
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft | fcs/elevator-pos-rad
|
|
-1.122
|
|
</COEFFICIENT>
|
|
|
|
<!-- Peden -->
|
|
<COEFFICIENT NAME="Cmdf" TYPE="VECTOR">
|
|
Delta_pitching_moment_due_to_flap_deflection
|
|
4
|
|
fcs/flap-pos-deg
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/cbarw-ft
|
|
0 0
|
|
10 -0.0654
|
|
20 -0.0981
|
|
30 -0.1140
|
|
</COEFFICIENT>
|
|
|
|
</AXIS>
|
|
|
|
<AXIS NAME="YAW">
|
|
|
|
<!-- based on Roskam p.482, clamped to +/-20deg beta -->
|
|
<COEFFICIENT NAME="Cnb" TYPE="VECTOR">
|
|
Yaw_moment_due_to_beta
|
|
3
|
|
aero/beta-rad
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft
|
|
-0.349 -0.0205
|
|
0 0
|
|
0.349 0.0205
|
|
</COEFFICIENT>
|
|
|
|
<!-- Roskam p.482 -->
|
|
<COEFFICIENT NAME="Cnp" TYPE="VALUE">
|
|
Yaw_moment_due_to_roll_rate
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/p-aero-rad_sec
|
|
-0.0278
|
|
</COEFFICIENT>
|
|
|
|
<!-- Roskam p.482 -->
|
|
<COEFFICIENT NAME="Cnr" TYPE="VALUE">
|
|
Yaw_moment_due_to_yaw_rate
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | aero/bi2vel | velocities/r-aero-rad_sec
|
|
-0.0937
|
|
</COEFFICIENT>
|
|
|
|
<!-- Peden -->
|
|
<COEFFICIENT NAME="Cnda" TYPE="VALUE">
|
|
Yaw_moment_due_to_aileron
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/left-aileron-pos-rad
|
|
-0.0053
|
|
</COEFFICIENT>
|
|
|
|
<!-- Peden -->
|
|
<COEFFICIENT NAME="Cndr" TYPE="VALUE">
|
|
Yaw_moment_due_to_rudder
|
|
aero/qbar-psf | metrics/Sw-sqft | metrics/bw-ft | fcs/rudder-pos-rad
|
|
-0.043
|
|
</COEFFICIENT>
|
|
|
|
</AXIS>
|
|
|
|
</AERODYNAMICS>
|
|
|
|
<!--
|
|
OUTPUT section definition
|
|
|
|
The following specifies the way that JSBSim writes out data.
|
|
|
|
NAME is the filename you want the output to go to
|
|
|
|
TYPE can be:
|
|
CSV Comma separated data. If a filename is supplied then the data
|
|
goes to that file. If COUT or cout is specified, the data goes
|
|
to stdout. If the filename is a null filename the data goes to
|
|
stdout, as well.
|
|
SOCKET Will eventually send data to a socket output, where NAME
|
|
would then be the IP address of the machine the data should be
|
|
sent to. DON'T USE THIS YET!
|
|
TABULAR Columnar data. NOT IMPLEMENTED YET!
|
|
TERMINAL Output to terminal. NOT IMPLEMENTED YET!
|
|
NONE Specifies to do nothing. THis setting makes it easy to turn on and
|
|
off the data output without having to mess with anything else.
|
|
|
|
The arguments that can be supplied, currently, are
|
|
|
|
RATE_IN_HZ An integer rate in times-per-second that the data is output. This
|
|
value may not be *exactly* what you want, due to the dependence
|
|
on dt, the cycle rate for the FDM.
|
|
|
|
The following parameters tell which subsystems of data to output:
|
|
|
|
SIMULATION ON|OFF
|
|
ATMOSPHERE ON|OFF
|
|
MASSPROPS ON|OFF
|
|
AEROSURFACES ON|OFF
|
|
RATES ON|OFF
|
|
VELOCITIES ON|OFF
|
|
FORCES ON|OFF
|
|
MOMENTS ON|OFF
|
|
POSITION ON|OFF
|
|
COEFFICIENTS ON|OFF
|
|
GROUND_REACTIONS ON|OFF
|
|
FCS ON|OFF
|
|
PROPULSION ON|OFF
|
|
|
|
NOTE that Time is always output with the data.
|
|
-->
|
|
<OUTPUT NAME="JSBout172.csv" TYPE="NONE">
|
|
RATE_IN_HZ 20
|
|
SIMULATION OFF
|
|
ATMOSPHERE ON
|
|
MASSPROPS ON
|
|
AEROSURFACES ON
|
|
RATES ON
|
|
VELOCITIES ON
|
|
FORCES ON
|
|
MOMENTS ON
|
|
POSITION ON
|
|
COEFFICIENTS ON
|
|
GROUND_REACTIONS ON
|
|
FCS ON
|
|
PROPULSION ON
|
|
</OUTPUT>
|
|
</FDM_CONFIG>
|