Path: Orbit/OrbitCoord
% Transforms modified equinoctial elements to Keplerian 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 and w is argument of perigee. -------------------------------------------------------------------------- Form: el = MEqToEl( x, mu ) -------------------------------------------------------------------------- ------ Inputs ------ x (6,:) Modified equinoctial elements [p;f;g;h;k;L] mu (1,1) Gravitational parameter ------- Outputs ------- el (6,:) Keplerian elements [a;i;W;w;e;M] --------------------------------------------------------------------------
Orbit: OrbitCoord/ElToMEq SC: BasicOrbit/Nu2M
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