Path: Orbit/OrbitMechanics
% Convert semi-major and semi-minor lengths to a and e Type MajorMinorToAE( sMin, sMaj ) for a demo. -------------------------------------------------------------------------- Form: [a,e] = MajorMinorToAE( sMin, sMaj ) -------------------------------------------------------------------------- ------ Inputs ------ sMin (1,:) Semi-minor axis sMaj (1,:) Semi-major axis ------- Outputs ------- sMaj (1,:) Semi-major e (1,:) Eccentricity --------------------------------------------------------------------------