OrbMnvrInclination:

Path: Orbit/OrbitManeuver

% Computes the delta-V for an inclination correction.
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   Form:
   deltaV = OrbMnvrInclination( v, e, nu, deltaI, mu )
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   ------
   Inputs
   ------
   v           (1,1)  Velocity
   e           (1,1)  Orbit eccentricity
   nu          (1,1)  True anomaly (rad)
   deltaI      (1,1)  Change in inclination (rad)
   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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