Path: SCPro/DynamicalModels
% Simulate a 2D orbit with aerodynamics
Uses CLCDFreeMolecular for lift and drag coefficients
Type PropagateOrbit2DAero for a demo
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Form:
x = PropagateOrbit2DAero( x, t, d )
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Inputs
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x (4,1) [r;v] (km,km/s)
t (1,:) Time vector
d (.) Data structure describing spacecraft model
.m (1,1) Mass (kg);
.a (1,1) Area (m^2)
.beta (1,1) Angle of attack (rad)
.tW (1,1) Surface temperature (deg-K_
.mW (1,1) Mean atmosphere molecular weight
.mu (1,1) Gravitational constant (m^3/s^2)
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Outputs
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x (4,1) d[r;v]/dt (km/s,km/s^2)
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