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Path: Orbit/OrbitCoord
% Converts R and V to a, e, rP and rA. -------------------------------------------------------------------------- Form: [a, e, rP, rA] = RV2AE( r, v, mu ) -------------------------------------------------------------------------- ------ Inputs ------ r (3,:) Position vector v (3,:) Velocity vector mu Gravitational constant ------- Outputs ------- a (1,:) Semi-major axis e (1,:) Eccentricity rP (1,:) Perigee rA (1,:) Apogee -------------------------------------------------------------------------- References: Bate, R.R., et. al. Fundamentals of Astrodynamics, pp. 70-71. --------------------------------------------------------------------------
Common: Graphics/Plot2D Math: Linear/Cross Math: Linear/Dot Math: Linear/DupVect Math: Linear/Mag
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