OrbMnvrOneTangent:

Path: Orbit/OrbitManeuver

% Computes the delta-V for a one-tangent transfer between coplanar orbits.
   The maneuver starts at E = 0 for the transfer orbit.
   Will perform a demo from LEO to GEO if given less than 4 inputs.
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   Form:
   [deltaV, tOF] = OrbMnvrOneTangent( rI, rF, nuT, type, mu )
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   ------
   Inputs
   ------
   rI          (1,1)  Initial radius
   rF          (1,1)  Final radius
   nuT         (1,1)  True anomaly between initial and final burn
   type        (1,1)  Either 'apoapsis' or 'periapsis'
   mu          (1,1)  Gravitational parameter

   -------
   Outputs
   -------
   deltaV      (1,1)  Delta-V data structure. 
                      .total (1,1)	Total required delta-V
                      .a     (1,1) Delta-V at point a
                      .b     (1,1) Delta-V at point b
   tOF         (1,1)  Time of flight

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   Reference: Vallado, D. A. (1997.) Fundamentals of Astrodynamics and
              Applications. pp 287-292.
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