PeriodToSMA:

Path: SC/BasicOrbit

% Compute the semi major axis from the period

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   Form:
   a = PeriodToSMA( T, mu )
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   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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