Path: ACPro/ACPointMass
% Simulate a point mass aircraft model in 2 dimensions.
This model requires drag and thrust functions to be passed as part
of the data structure. The thrust function is of the form
[thrust, sFC] = ThrustFunction( m, d, p )
where thrust is the scalar thrust. The drag function is of the form
[lift, drag] = DragFunction( m, d ),
where d is a data structure and drag is the scalar drag.
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Form:
d = RHS2DPointMass;
xDot = RHS2DPointMass( x, t, d )
[thrust, drag] = RHS2DPointMass( x, t, d )
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Inputs
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x (5,1) [v;gamma;h;mass;range]
t (1,1) Time vector for integration
d (1,1) Data structure
.tFcn (1,1) Pointer to thrust function
.g (1,1) Gravitational acceleration
.engine (1,1) Structure to engine data
.aero (1,1) Structure to aero data
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Outputs
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if 1 output:
xDot (5,1) d[v;gamma;h;mass;range]/dt
if 2 outputs
thrust (1,1) Thrust
drag (1,1) Drag
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ACPro: ACPointMass/SimpleLiftAndDrag AerospaceUtils: AeroData/AtmData 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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