CircularOrbitState:

Path: Orbit/OrbitCoord

% Compute inertial position and velocity given circular orbit elements
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   Form:
   [r,v] = CircularOrbitState( R, inc, ra, M, n );
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   ------
   Inputs
   ------
   R           (1,:)    Distance from planet center 
   inc         (1,1)    Inclination [rad]
   ra          (1,1)    Right ascension [rad]
   M           (1,:)    Mean anomaly [rad]
   n           (1,:)    Orbit rate

   -------
   Outputs
   -------
   lat         (1)       Latitude  [deg]
   lon         (1)       Longitude [deg]
   alt         (1)       Altitude  [km]

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