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Path: Orbit/OrbitCoord
% Converts semi-major axis and eccentricity to right perigee and apogee. -------------------------------------------------------------------------- Form: [rP, rA] = AE2RPRA( a, e ) -------------------------------------------------------------------------- ------ Inputs ------ a (1,1) Semi-major axis e (1,1) Eccentricity ------- Outputs ------- rP (1,1) Perigee rA (1,1) Apogee --------------------------------------------------------------------------
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