107 lines
3 KiB
Text
107 lines
3 KiB
Text
|
AISim uses a 6-degree of freedom, linear coefficient resolver model.
|
||
|
|
|
||
|
|
|
||
|
|
All units are imperial.
|
||
|
|
The aero reference point is always located at (0.0, 0.0, 0.0).
|
||
|
|
Center of gravity is relative to the aero reference point.
|
||
|
|
All other positions are relative to the center of gravity.
|
||
|
|
|
||
|
|
Positions are in inches and in the JSBSim structural frame:
|
||
|
|
X is positive aft
|
||
|
|
Y is positive right
|
||
|
|
Z is positive up
|
||
|
|
|
||
|
|
Up to 4 engines and up to 4 gear positions (contact points) can be defined.
|
||
|
|
AISim always adds an extra contact point at the aero reference point.
|
||
|
|
|
||
|
|
Configuration files are in JSON format.
|
||
|
|
Any parameter which is omitted is set to zero.
|
||
|
|
|
||
|
|
AeromatiC++ version 3.3.12 or later also outputs to AISim JSON format.
|
||
|
|
|
||
|
|
An example of a configuration file for the Cessna 172p is given below.
|
||
|
|
Note that JSON does not support comments. So the semicolon and text following
|
||
|
|
it in this example are just for clarity and should be removed or omitted when
|
||
|
|
using it with AISim.
|
||
|
|
=============================================================================
|
||
|
|
{
|
||
|
|
"c172p" : 1.0, ; name and version number
|
||
|
|
|
||
|
|
"Sw" : 174.0, ; wing area (ft2)
|
||
|
|
"cbar" : 5.3, ; root chord (ft)
|
||
|
|
"bw" : 35.8, ; wing span (ft)
|
||
|
|
|
||
|
|
"mass" : 2300.0, ; mass (lbs)
|
||
|
|
"Ixx" : 948.0, ; inertia along the x axis (slug*ft2)
|
||
|
|
"Iyy" : 1346.0, ; inertia along the y axis (slug*ft2)
|
||
|
|
"Izz" : 1967.0, ; inertia along the z axis (slug*ft2)
|
||
|
|
"Ixz" : 0.0, ; inertia along the xz axis (slug*ft2)
|
||
|
|
|
||
|
|
"cg" : [ -2.4, 0.0, 22.9 ], ; CG relative to AR (in)
|
||
|
|
|
||
|
|
"engine" : [
|
||
|
|
{
|
||
|
|
"pos" : [ -78.7, 0.0, 22.9 ], ; enginge pos relative to CG (in)
|
||
|
|
"dir" : [ 0.0, 0.0, 0.0 ], ; thruster direction (degrees)
|
||
|
|
|
||
|
|
"FT_max" : 615.6, ; max thrust at sea level (lbs)
|
||
|
|
"MT_max" : -37.3, ; max thruster torque (lb-ft)
|
||
|
|
"rpm_max" : 3002.1 ; max propeller revolutions per minute
|
||
|
|
} ],
|
||
|
|
|
||
|
|
"gear" : [
|
||
|
|
{
|
||
|
|
"pos" : [ -90.3, 0.0, -56.7 ], ; gear pos relative to CG (in)
|
||
|
|
"spring" : 690.0, ; gear spring factor (lbs/ft)
|
||
|
|
"damp" : 345.0 ; gear damping factor (lbs/ft/sec)
|
||
|
|
},
|
||
|
|
{
|
||
|
|
"pos" : [ 5.3, -38.7, -56.7 ],
|
||
|
|
"spring" : 2300.0,
|
||
|
|
"damp" : 1150.0
|
||
|
|
},
|
||
|
|
{
|
||
|
|
"pos" : [ 5.3, 38.7, -56.7 ],
|
||
|
|
"spring" : 2300.0,
|
||
|
|
"damp" : 1150.0
|
||
|
|
} ],
|
||
|
|
|
||
|
|
"de_max" : 17.5, ; max elevator deflection (degrees)
|
||
|
|
"dr_max" : 20.0, ; max rudder deflection (degrees)
|
||
|
|
"da_max" : 20.0, ; max aileron deflection (degrees)
|
||
|
|
"df_max" : 40.0, ; max flap deflection (degrees)
|
||
|
|
|
||
|
|
"CLmin" : 0.31,
|
||
|
|
"CLa" : 5.143,
|
||
|
|
"CLadot" : 1.7,
|
||
|
|
"CLq" : 3.9,
|
||
|
|
"CLdf" : 0.4000,
|
||
|
|
|
||
|
|
"CDmin" : 0.031,
|
||
|
|
"CDa" : 0.1581,
|
||
|
|
"CDb" : 0.17,
|
||
|
|
"CDi" : 0.054,
|
||
|
|
"CDdf" : 0.0300,
|
||
|
|
|
||
|
|
"CYb" : -0.31,
|
||
|
|
"CYp" : 0.037,
|
||
|
|
"CYr" : 0.21,
|
||
|
|
"CYdr" : 0.187,
|
||
|
|
|
||
|
|
"Clb" : -0.089,
|
||
|
|
"Clp" : -0.47,
|
||
|
|
"Clr" : 0.096,
|
||
|
|
"Clda" : 0.178,
|
||
|
|
"Cldr" : 0.0147,
|
||
|
|
|
||
|
|
"Cma" : -0.89,
|
||
|
|
"Cmadot" : -5.2,
|
||
|
|
"Cmq" : -12.4,
|
||
|
|
"Cmde" : -1.28,
|
||
|
|
|
||
|
|
"Cnb" : 0.065,
|
||
|
|
"Cnp" : -0.03,
|
||
|
|
"Cnr" : -0.099,
|
||
|
|
"Cndr" : -0.0657
|
||
|
|
}
|