Path: Orbit/OrbitCoord
% Transforms Keplerian elements to modified equinoctial elements. 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 = ElToMEq( el, mu ) -------------------------------------------------------------------------- ------ Inputs ------ el (6,1) Keplerian elements mu (1,1) Gravitational parameter ------- Outputs ------- x (6,1) Elements --------------------------------------------------------------------------
SC: BasicOrbit/M2Nu
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