593 lines
18 KiB
XML
593 lines
18 KiB
XML
<FDM_CONFIG NAME="c172" VERSION="1.58">
|
|
<!--
|
|
|
|
File: c172p.xml (originally c172.xml)
|
|
Author: Tony Peden
|
|
CVS Version: $Id$
|
|
|
|
Function: Models a 1981 Cessna 172P.
|
|
Notes: Try running FlightGear using this command line,
|
|
fgfs --aircraft=c172p
|
|
-->
|
|
|
|
<METRICS>
|
|
<!--
|
|
// Wing area (ft^2)
|
|
// Wing span (ft)
|
|
// Wing avg. chord (ft)
|
|
// H. Tail Area (ft^2)
|
|
// Wing MAC to H.Tail MAC (ft)
|
|
// V. Tail Area (ft^2)
|
|
// Wing MAC to V.Tail MAC (ft)
|
|
// Ixx
|
|
// Iyy
|
|
// Izz
|
|
// Ixz
|
|
// Empty weight
|
|
// Center of gravity location, empty weight, in aircraft's own structural coord
|
|
// system. X, Y, Z, in inches
|
|
// Pilot's eyepoint location, in aircraft's own coord system, FROM cg.
|
|
// X, Y, Z, in inches
|
|
AC_AERORP 43.2 0.0 59.4
|
|
-->
|
|
|
|
AC_WINGAREA 174 <!-- square feet -->
|
|
AC_WINGSPAN 35.8 <!-- ft -->
|
|
AC_CHORD 4.9 <!-- ft -->
|
|
AC_HTAILAREA 21.9 <!-- square feet -->
|
|
AC_HTAILARM 15.7 <!-- ft -->
|
|
AC_VTAILAREA 16.5 <!-- square feet -->
|
|
AC_LV 15.7 <!-- ft -->
|
|
AC_IXX 948
|
|
AC_IYY 1346
|
|
AC_IZZ 1967
|
|
AC_IXZ 0
|
|
AC_EMPTYWT 1500
|
|
AC_AERORP 43.2 0.0 59.4
|
|
AC_CGLOC 41.0 0.0 36.5
|
|
<!-- Pilot -->
|
|
AC_POINTMASS 180.0 36.0 -14.0 24.0
|
|
<!-- Co-pilot -->
|
|
<!-- AC_POINTMASS 180.0 36.0 14.0 24.0 -->
|
|
AC_EYEPTLOC 37.0 0.0 48.0
|
|
|
|
</METRICS>
|
|
|
|
<UNDERCARRIAGE>
|
|
|
|
<!--
|
|
The gear parameters that can be specified are as follows, IN ORDER OF APPEARANCE:
|
|
|
|
AC_GEAR
|
|
<name> name of gear entry - no spaces allowed
|
|
<X> <Y> <Z> Gear location in aircraft body coords in inches
|
|
<spring constant> spring constant in lbs/ft
|
|
<damping coefficient> damping coefficient in lbs/ft/sec
|
|
<dynamic friction coefficient> Self-explanatory: sliding friction coefficient
|
|
<static friction coefficient> Self-explanatory: "onset" friction coefficient
|
|
<rolling friction coefficient> Self-explanatory: rolling friction coefficient
|
|
<steerability attribute> One of <STEERABLE | FIXED | CASTERED>
|
|
<brake group membership> One of <LEFT | CENTER | RIGHT | NOSE | TAIL | NONE>
|
|
<max steer angle> Maximum steerable angle in degrees
|
|
<retraction attribute> <RETRACT | FIXED>
|
|
-->
|
|
|
|
AC_GEAR NOSE -6.8 0.0 -20.0 1800 600 0.5 0.8 0.02 STEERABLE NOSE 20 FIXED
|
|
AC_GEAR LEFT_MAIN 58.2 -43.0 -17.9 5400 1600 0.5 0.8 0.02 FIXED LEFT 0 FIXED
|
|
AC_GEAR RIGHT_MAIN 58.2 43.0 -17.9 5400 1600 0.5 0.8 0.02 FIXED RIGHT 0 FIXED
|
|
AC_GEAR TAIL_SKID 188.0 0.0 8.0 20000 1000 0.2 0.2 0.2 FIXED NONE 0 FIXED
|
|
AC_GEAR LEFT_TIP 43.2 -214.8 59.4 10000 2000 0.2 0.2 0.2 FIXED NONE 0 FIXED
|
|
AC_GEAR RIGHT_TIP 43.2 214.8 59.4 10000 2000 0.2 0.2 0.2 FIXED NONE 0 FIXED
|
|
|
|
</UNDERCARRIAGE>
|
|
|
|
<PROPULSION>
|
|
|
|
<!--
|
|
TANKS SECTION
|
|
|
|
Tank locations and characteristics, empty weight, in aircraft's own coord system:
|
|
X, Y, Z, in inches
|
|
effective radius of tank, in inches (for fuel slosh, if/when modeled)
|
|
capacity in pounds
|
|
Current contents, in pounds
|
|
|
|
ENGINE[S] SECTION
|
|
|
|
Engine[s] is|are specified by giving engine name (which corresponds to an engine
|
|
definition file in the "engines" directory) followed by x, y, z placement and
|
|
pitch and yaw orientation. Coordinates are given in inches in the structural
|
|
coordinate frame. Angles for pitch and yaw are specified in radians.
|
|
|
|
AC_ENGINE name x y z pitch yaw
|
|
|
|
THRUSTER[S] SECTION
|
|
|
|
AC_THRUSTER name x y z pitch yaw
|
|
-->
|
|
|
|
<AC_ENGINE FILE="eng_io320">
|
|
XLOC -19.7
|
|
YLOC 0.0
|
|
ZLOC 26.6
|
|
PITCH 0.0
|
|
YAW 0.0
|
|
FEED 0
|
|
FEED 1
|
|
</AC_ENGINE>
|
|
|
|
<AC_THRUSTER FILE="prop_75in2f">
|
|
XLOC -37.7
|
|
YLOC 0.0
|
|
ZLOC 26.6
|
|
PITCH 0.0
|
|
YAW 0
|
|
P_FACTOR 10.0
|
|
SENSE 1.0
|
|
</AC_THRUSTER>
|
|
|
|
<AC_TANK TYPE="FUEL" NUMBER="0">
|
|
XLOC 56.0
|
|
YLOC -112.0
|
|
ZLOC 59.4
|
|
RADIUS 29.4
|
|
CAPACITY 185.0
|
|
CONTENTS 100.0
|
|
</AC_TANK>
|
|
|
|
<AC_TANK TYPE="FUEL" NUMBER="1">
|
|
XLOC 56.0
|
|
YLOC 112.0
|
|
ZLOC 59.4
|
|
RADIUS 29.4
|
|
CAPACITY 185.0
|
|
CONTENTS 100.0
|
|
</AC_TANK>
|
|
|
|
</PROPULSION>
|
|
|
|
|
|
<FLIGHT_CONTROL NAME="c172">
|
|
<COMPONENT NAME="Pitch Trim Sum" TYPE="SUMMER">
|
|
ID 0
|
|
INPUT FG_ELEVATOR_CMD
|
|
INPUT FG_PITCH_TRIM_CMD
|
|
CLIPTO -1 1
|
|
</COMPONENT>
|
|
<COMPONENT NAME="Elevator Control" TYPE="AEROSURFACE_SCALE">
|
|
ID 1
|
|
INPUT 0
|
|
MIN -28
|
|
MAX 23
|
|
OUTPUT FG_ELEVATOR_POS
|
|
GAIN 0.01745
|
|
</COMPONENT>
|
|
<COMPONENT NAME="Roll Trim Sum" TYPE="SUMMER">
|
|
ID 2
|
|
INPUT FG_AILERON_CMD
|
|
INPUT FG_ROLL_TRIM_CMD
|
|
CLIPTO -1 1
|
|
</COMPONENT>
|
|
<COMPONENT NAME="Left Aileron Control" TYPE="AEROSURFACE_SCALE">
|
|
ID 3
|
|
INPUT 2
|
|
MIN -20
|
|
MAX 15
|
|
GAIN 0.01745
|
|
OUTPUT FG_LEFT_AILERON_POS
|
|
</COMPONENT>
|
|
<COMPONENT NAME="Right Aileron Control" TYPE="AEROSURFACE_SCALE">
|
|
ID 4
|
|
INPUT 2
|
|
MIN -20
|
|
MAX 15
|
|
INVERT
|
|
GAIN 0.01745
|
|
OUTPUT FG_RIGHT_AILERON_POS
|
|
</COMPONENT>
|
|
<COMPONENT NAME="Yaw Trim Sum" TYPE="SUMMER">
|
|
ID 5
|
|
INPUT FG_RUDDER_CMD
|
|
INPUT FG_YAW_TRIM_CMD
|
|
CLIPTO -1 1
|
|
</COMPONENT>
|
|
<COMPONENT NAME="Rudder Control" TYPE="AEROSURFACE_SCALE">
|
|
ID 6
|
|
INPUT 5
|
|
MIN -16
|
|
MAX 16
|
|
GAIN 0.01745
|
|
OUTPUT FG_RUDDER_POS
|
|
</COMPONENT>
|
|
<COMPONENT NAME="Flaps Control" TYPE="KINEMAT">
|
|
ID 7
|
|
INPUT FG_FLAPS_CMD
|
|
DETENTS 4
|
|
0 0
|
|
10 2
|
|
20 1
|
|
30 1
|
|
OUTPUT FG_FLAPS_POS
|
|
</COMPONENT>
|
|
</FLIGHT_CONTROL>
|
|
|
|
<AERODYNAMICS>
|
|
|
|
AC_ALPHALIMITS -0.087 0.28
|
|
AC_HYSTLIMITS 0.09 0.36
|
|
|
|
<AXIS NAME="LIFT">
|
|
<GROUP NAME="CLb">
|
|
Basic_lift
|
|
<FACTOR NAME="kCLge" TYPE="VECTOR">
|
|
Change_in_lift_due_to_ground_effect
|
|
13
|
|
FG_HOVERB
|
|
FG_NONE
|
|
0.0 1.203
|
|
0.1 1.127
|
|
0.15 1.090
|
|
0.2 1.073
|
|
0.3 1.046
|
|
0.4 1.055
|
|
0.5 1.019
|
|
0.6 1.013
|
|
0.7 1.008
|
|
0.8 1.006
|
|
0.9 1.003
|
|
1.0 1.002
|
|
1.1 1.0
|
|
</FACTOR>
|
|
<COEFFICIENT NAME="CLwbh" TYPE="TABLE">
|
|
Lift_due_to_alpha
|
|
17
|
|
2
|
|
FG_ALPHA
|
|
FG_HYSTPARM
|
|
FG_QBAR|FG_WINGAREA
|
|
0 1
|
|
-0.09 -0.22 -0.22
|
|
0 0.25 0.25
|
|
0.09 0.73 0.73
|
|
0.1 0.83 0.78
|
|
0.12 0.92 0.79
|
|
0.14 1.02 0.81
|
|
0.16 1.08 0.82
|
|
0.17 1.13 0.83
|
|
0.19 1.19 0.85
|
|
0.21 1.25 0.86
|
|
0.24 1.35 0.88
|
|
0.26 1.44 0.9
|
|
0.28 1.47 0.92
|
|
0.3 1.43 0.95
|
|
0.32 1.38 0.99
|
|
0.34 1.3 1.05
|
|
0.36 1.15 1.15
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="CLDf" TYPE="VECTOR">
|
|
Delta_lift_due_to_flap_deflection
|
|
4
|
|
FG_FLAPS_POS
|
|
FG_QBAR|FG_WINGAREA
|
|
0 0
|
|
10 0.20
|
|
20 0.30
|
|
30 0.35
|
|
</COEFFICIENT>
|
|
</GROUP>
|
|
<COEFFICIENT NAME="CLDe" TYPE="VALUE">
|
|
Lift_due_to_Elevator_Deflection
|
|
FG_QBAR|FG_WINGAREA|FG_ELEVATOR_POS
|
|
0.347
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="CLadot" TYPE="VALUE">
|
|
Lift_due_to_alpha_rate
|
|
FG_QBAR|FG_WINGAREA|FG_ALPHADOT|FG_CI2VEL
|
|
1.7
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="CLq" TYPE="VALUE">
|
|
Lift_due_to_pitch_rate
|
|
FG_QBAR|FG_WINGAREA|FG_AEROQ|FG_CI2VEL
|
|
3.9
|
|
</COEFFICIENT>
|
|
</AXIS>
|
|
<AXIS NAME="DRAG">
|
|
<COEFFICIENT NAME="CDo" TYPE="VALUE">
|
|
Drag_at_zero_lift
|
|
FG_QBAR|FG_WINGAREA
|
|
0.026
|
|
</COEFFICIENT>
|
|
<GROUP NAME="CDb">
|
|
Basic_drag
|
|
<FACTOR NAME="kCDge" TYPE="VECTOR">
|
|
Change_in_drag_due_to_ground_effect
|
|
13
|
|
FG_HOVERB
|
|
FG_NONE
|
|
0.0 0.048
|
|
0.1 0.515
|
|
0.15 0.629
|
|
0.2 0.709
|
|
0.3 0.815
|
|
0.4 0.882
|
|
0.5 0.928
|
|
0.6 0.962
|
|
0.7 0.988
|
|
0.8 1.0
|
|
0.9 1.0
|
|
1.0 1.0
|
|
1.1 1.0
|
|
</FACTOR>
|
|
<COEFFICIENT NAME="CDDf" TYPE="VECTOR">
|
|
Delta_drag_due_to_flap_deflection
|
|
4
|
|
FG_FLAPS_POS
|
|
FG_QBAR|FG_WINGAREA
|
|
0 0
|
|
10 0.007
|
|
20 0.012
|
|
30 0.018
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="CDwbh" TYPE="TABLE">
|
|
Drag_due_to_alpha
|
|
26
|
|
4
|
|
FG_ALPHA
|
|
FG_FLAPS_POS
|
|
FG_QBAR|FG_WINGAREA
|
|
0 10 20 30
|
|
-0.0872664 0.00407143 3.8165e-05 0.000512444 0.00137231
|
|
-0.0698132 0.0013424 0.000440634 0.00248067 0.00412341
|
|
-0.0523599 8.96747e-05 0.00231942 0.0059252 0.00835082
|
|
-0.0349066 0.000313268 0.00567451 0.0108461 0.0140545
|
|
-0.0174533 0.00201318 0.0105059 0.0172432 0.0212346
|
|
0 0.0051894 0.0168137 0.0251167 0.0298909
|
|
0.0174533 0.00993967 0.0247521 0.0346492 0.0402205
|
|
0.0349066 0.0162201 0.0342207 0.0457119 0.0520802
|
|
0.0523599 0.0240308 0.0452195 0.0583047 0.0654701
|
|
0.0698132 0.0333717 0.0577485 0.0724278 0.0803902
|
|
0.0872664 0.0442427 0.0718077 0.088081 0.0968405
|
|
0.10472 0.056644 0.0873971 0.105265 0.114821
|
|
0.122173 0.0705754 0.104517 0.123978 0.134332
|
|
0.139626 0.086037 0.123166 0.144222 0.155373
|
|
0.15708 0.096239 0.135317 0.157346 0.168984
|
|
0.174533 0.106859 0.147857 0.170848 0.182966
|
|
0.191986 0.118034 0.160954 0.184905 0.197503
|
|
0.209439 0.129765 0.174606 0.199517 0.212596
|
|
0.226893 0.142366 0.189176 0.215072 0.228643
|
|
0.244346 0.156452 0.205363 0.23231 0.246406
|
|
0.261799 0.172732 0.223956 0.252059 0.266733
|
|
0.279253 0.178209 0.230187 0.258667 0.273529
|
|
0.296706 0.171598 0.222665 0.25069 0.265325
|
|
0.314159 0.161786 0.211468 0.2388 0.253089
|
|
0.331613 0.147493 0.19508 0.221364 0.235129
|
|
0.349066 0.109678 0.151171 0.174408 0.186649
|
|
</COEFFICIENT>
|
|
</GROUP>
|
|
<COEFFICIENT NAME="CDDe" TYPE="VALUE">
|
|
Drag_due_to_Elevator_Deflection
|
|
FG_QBAR|FG_WINGAREA|FG_AELEVATOR_POS
|
|
0.06
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="CDbeta" TYPE="VALUE">
|
|
Drag_due_to_sideslip
|
|
FG_QBAR|FG_WINGAREA|FG_ABETA
|
|
0.17
|
|
</COEFFICIENT>
|
|
|
|
</AXIS>
|
|
|
|
<AXIS NAME="SIDE">
|
|
<COEFFICIENT NAME="CYb" TYPE="VECTOR">
|
|
Side_force_due_to_beta
|
|
3
|
|
FG_BETA
|
|
FG_QBAR|FG_WINGAREA
|
|
-0.349 0.108
|
|
0 0
|
|
0.349 -0.108
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="CYda" TYPE="VALUE">
|
|
Side_force_due_to_aileron
|
|
FG_QBAR|FG_WINGAREA|FG_AILERON_POS
|
|
-0.05
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="CYdr" TYPE="VALUE">
|
|
Side_force_due_to_rudder
|
|
FG_QBAR|FG_WINGAREA|FG_RUDDER_POS
|
|
0.098
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="CYp" TYPE="VALUE">
|
|
Side_force_due_to_roll_rate
|
|
FG_QBAR|FG_WINGAREA|FG_BI2VEL|FG_AEROP
|
|
-0.037
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="CYr" TYPE="VALUE">
|
|
Side_force_due_to_yaw_rate
|
|
FG_QBAR|FG_WINGAREA|FG_BI2VEL|FG_AEROR
|
|
0.21
|
|
</COEFFICIENT>
|
|
</AXIS>
|
|
|
|
<AXIS NAME="ROLL">
|
|
<COEFFICIENT NAME="Clb" TYPE="VECTOR">
|
|
Roll_moment_due_to_beta
|
|
3
|
|
FG_BETA
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN
|
|
-0.349 0.0311
|
|
0 0
|
|
0.349 -0.0311
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="Clp" TYPE="VALUE">
|
|
Roll_moment_due_to_roll_rate_(roll_damping)
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_BI2VEL|FG_AEROP
|
|
-0.47
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="Clr" TYPE="VECTOR">
|
|
Roll_moment_due_to_yaw_rate
|
|
2
|
|
FG_ALPHA
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_BI2VEL|FG_AEROR
|
|
0.000 0.08
|
|
0.094 0.19
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="Clda" TYPE="VALUE">
|
|
Roll_moment_due_to_aileron
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_AILERON_POS
|
|
0.23
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="Cldr" TYPE="VALUE">
|
|
Roll_moment_due_to_rudder
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_RUDDER_POS
|
|
0.0147
|
|
</COEFFICIENT>
|
|
|
|
</AXIS>
|
|
|
|
<AXIS NAME="PITCH">
|
|
|
|
<COEFFICIENT NAME="Cmalpha" TYPE="VALUE">
|
|
Pitch_moment_due_to_alpha
|
|
FG_QBAR|FG_WINGAREA|FG_CBAR|FG_ALPHA
|
|
-1.8
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="CmDf" TYPE="VECTOR">
|
|
Delta_pitching_moment_due_to_flap_deflection
|
|
4
|
|
FG_FLAPS_POS
|
|
FG_QBAR|FG_WINGAREA|FG_CBAR
|
|
0 0
|
|
10 -0.0654
|
|
20 -0.0981
|
|
30 -0.1140
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="Cmq" TYPE="VALUE">
|
|
Pitch_moment_due_to_pitch_rate
|
|
FG_QBAR|FG_WINGAREA|FG_CBAR|FG_CI2VEL|FG_AEROQ
|
|
-12.4
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="Cmadot" TYPE="VALUE">
|
|
Pitch_moment_due_to_alpha_rate
|
|
FG_QBAR|FG_WINGAREA|FG_CBAR|FG_CI2VEL|FG_ALPHADOT
|
|
-5.2
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="Cmo" TYPE="VALUE">
|
|
Pitching_moment_at_zero_alpha
|
|
FG_QBAR|FG_WINGAREA|FG_CBAR
|
|
0.1
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="Cmde" TYPE="VALUE">
|
|
Pitch_moment_due_to_elevator_deflection
|
|
FG_QBAR|FG_WINGAREA|FG_CBAR|FG_ELEVATOR_POS
|
|
-1.28
|
|
</COEFFICIENT>
|
|
|
|
</AXIS>
|
|
|
|
<AXIS NAME="YAW">
|
|
|
|
<COEFFICIENT NAME="Cnb" TYPE="VECTOR">
|
|
Yaw_moment_due_to_beta
|
|
3
|
|
FG_BETA
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN
|
|
-0.349 -0.0227
|
|
0 0
|
|
0.349 0.0227
|
|
</COEFFICIENT>
|
|
<COEFFICIENT NAME="Cnp" TYPE="VALUE">
|
|
Yaw_moment_due_to_roll_rate
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_BI2VEL|FG_AEROP
|
|
-0.03
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="Cnr" TYPE="VALUE">
|
|
Yaw_moment_due_to_yaw_rate
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_BI2VEL|FG_AEROR
|
|
-0.099
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="Cnda" TYPE="VALUE">
|
|
Yaw_moment_due_to_aileron
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_AILERON_POS
|
|
0.0053
|
|
</COEFFICIENT>
|
|
|
|
<COEFFICIENT NAME="Cndr" TYPE="VALUE">
|
|
Yaw_moment_due_to_rudder
|
|
FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_RUDDER_POS
|
|
-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>
|
|
|