OrbMnvrSemimajor:

Path: Orbit/OrbitManeuver

% Computes the delta-V for a change in semi-major axis.
   Will perform a demo for a low earth orbit.
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   Form:
   deltaV = OrbMnvrSemimajor( v, a, deltaA, mu )
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   ------
   Inputs
   ------
   v           (1,1)  Velocity
   a           (1,1)  Semimajor axis
   deltaA      (1,1)  Change in semimajor axis
   mu          (1,1)  Gravitational parameter

   -------
   Outputs
   -------
   deltaV      (1,1)  Delta-V data structure. 
                      .total (1,1)	Total required delta-V

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   Reference: Vallado, D. A. (1997.) Fundamentals of Astrodynamics and
              Applications. p. 300.
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