Path: Orbit/OrbitCoord
% Converts semi-major axis and eccentricity to right perigee and apogee. -------------------------------------------------------------------------- Form: [rP, rA] = AE2RPRA( a, e ) -------------------------------------------------------------------------- ------ Inputs ------ a (1,:) Semi-major axis e (1,:) Eccentricity ------- Outputs ------- rP (1,:) Perigee rA (1,:) Apogee -------------------------------------------------------------------------- References: Bate, R.R., et. al. Fundamentals of Astrodynamics, pp. 70-71. --------------------------------------------------------------------------
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