Path: ACPro/ACPointMass
% 3D point aircraft model with time varying mass.
If a time constant for a control is set to zero it will make the
control and actual values the same and remove those states.
d.thrust can be a scalar, in which case mDot = 0 or a function of the
form:
[thrust, sFC] = d.thrust( mach, d, p );
where p is the standard atmosphere model and d is the data for the
engine model.
This routine uses meters for distance. With numerical integration
you just need the first output. The others are for getting
information about intermediate values.
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Form:
d = RHS3DPointAircraft;dg
[sDot, D, L, rho, thrust, mach, q, iSp] = RHS3DPointAircraft( s, t, d )
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Inputs
------
s (7,1) State [v;gamma;psi;x;y;h;m] (metric)
t (1,1) Time (s) (unused)
d (.) Data structure
.mass (1,1) Dry mass of the aircraft (kg)
.s (1,1) Reference area (m^2)
.cDCL (1,1) Lift and drag function or
(1,3) [cLAlpha, cD0, kInduced]
.lDData (.) Data to be passed to cDCL
.atmData (.) Data for StdAtm
.alpha (1,1) Angle of attack (rad)
.phi (1,1) Bank angle (rad)
.thrust (1,1) Thrust function pointer or thrust
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Outputs
-------
s (7,1) State derivative d[v;gamma;psi;x;y;h;gm]/dt
D (1,1) Drag
L (1,1) Lift
rho (1,1) Density
thrust (1,1) Engine thrust
q (1,1) Dynamic pressure
iSp (1,1) Engine specific impulse
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ACPro: ACPointMass/SimpleLiftAndDrag AerospaceUtils: AeroData/AtmData Common: Atmosphere/StdAtm Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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