Path: Orbit/OrbitCoord
% Transforms elements r and v to modified equinoctial. The modified equinoctial elements are p = a(1 + e^2) f = ecos(w + W); g = esin(w + W); h = tan(i/2)cosW k = tan(i/2)sinW L = W + w + nu W is right ascension of the ascending node w is argument of perigee -------------------------------------------------------------------------- Form: x = RVToMEq( r, v, mu ) -------------------------------------------------------------------------- ------ Inputs ------ r (3,1) Position vector v (3,1) Velocity vector mu (1,1) Gravitational parameter ------- Outputs ------- x (6,1) Elements --------------------------------------------------------------------------
Orbit: OrbitCoord/ElToMEq Orbit: OrbitCoord/MEqToRV SC: BasicOrbit/RV2El
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