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Path: Orbit/OrbitCoord
% Converts R and V to Equinoctial elements -------------------------------------------------------------------------- Form: eq = RV2Eq( r, v, mu ) -------------------------------------------------------------------------- ------ Inputs ------ r (3,1) Position vector v (3,1) Velocity vector mu Gravitational constant ------- Outputs ------- eq Elements vector [a,P1,P2,Q1,Q2,l] -------------------------------------------------------------------------- References: Bate, R.R., et. al. Fundamentals of Astrodynamics, pp. 70-71. --------------------------------------------------------------------------
Orbit: OrbitCoord/El2Eq SC: BasicOrbit/RV2El
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