Path: SC/BasicOrbit
% Compute the semi major axis from the period -------------------------------------------------------------------------- Form: a = PeriodToSMA( T, mu ) -------------------------------------------------------------------------- ------ Inputs ------ T (1,1) Orbit period (sec) mu (1,1) Gravitational constant (km^3/sec^2) Optional. Earth gravitational constant used if not provided. ------- Outputs ------- a (1,1) Semi major axis (km) --------------------------------------------------------------------------
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