Path: SC/BasicOrbit
% Right hand side for a simple orbit.
External disturbances may be passed in via the data structure.
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Form:
d = RHSOrbit; % data structure
xDot = RHSOrbit( x, t, d )
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Inputs
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x (6,1) Orbital state [r;v] in km and km/s
t (1,1) Time (unused)
d (.) Data structure
.mu (1,1) Gravitational constant
.a (3,1) Acceleration (km/s2)
.states {6} State names
.x0 (6,1) Initial state
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Outputs
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xDot (6,1) d[r;v]/dt
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Math: Linear/Mag
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