OrbMnvrLongAndIncl:

Path: Orbit/OrbitManeuver

% Delta-V for an longitude and inclination change maneuver for a circular orbit.
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   Form:
    [deltaV, u] = OrbMnvrLongAndIncl( v, iI, iF, deltaLon, mu )
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   ------
   Inputs
   ------
   v           (1,1)  Velocity
   iI          (1,1)  Initial orbit inclination (rad)
   iF          (1,1)  Final orbit inclination (rad)
   deltaLon    (1,1)  Change in longitude
   mu          (1,1)  Gravitational parameter

   -------
   Outputs
   -------
   deltaV      (1,1)  Delta-V data structure. 
                      .total (1,1)	Total required delta-V
   u           (1,1)  Argument of latitude for the common points
                      .final   (1,1) Final latitude (rad)
                      .initial (1,1) Initial latitude (rad)

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   Reference: Vallado, D. A. (1997.) Fundamentals of Astrodynamics and
              Applications. p. 306.
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