Path: Orbit/Optimization
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Computes sail partials using a first difference approximation
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Form:
f = EqPartials( x, d, thrust, dX )
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Inputs
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x (7,1) States [p;f;g;h;k;L;m]
d (1,1) Data structure
.mu (1,1) Gravitational coefficient
dX (1,1) delta
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Outputs
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f (7,7) The state partials
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Orbit: RHSOrbit/RHSEquinoctial
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