OptimalInPlaneDeltaV:

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   Computes the delta-v's and half-orbit delays for an in-plane maneuver.

   Since version 7.
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   Usage:
   [dV1,dV2,dV3,M,N] = OptimalInPlaneDeltaV( nOrbMin, nOrbMax, a, th0, th1, ...
                                       delta_a, delta_th0, delta_q1, delta_q2 );
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   Inputs
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   nOrbMin                (1)   Minimum number of orbits the maneuver may last
   nOrbMax                (1)   Maximum number of orbits the maneuver may last
   a                      (1)   Mean semi-major axis of reference      [km]
   th0                    (1)   Latitude of reference at measurement   [rad]
   th1                    (1)   Latitude at first burn                 [rad]
   delta_a                (1)   Error in semi-major axis difference    [km]
   delta_th0              (1)   Error in latitude difference           [rad]
   delta_q1               (1)   Error in q1 difference
   delta_q2               (1)   Error in q2 difference
   analyze                (1)   Flag indicating whether to analyze the
                                performance of this optimization (optional)

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   Outputs
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   dV1                    (1)   First delta-v                          [km/s]
   dV2                    (1)   Second delta-v                         [km/s]
   dV3                    (1)   Third delta-v                          [km/s]
   M                      (1)   Number of half-orbits between burn 1 and burn 2
   N                      (1)   Number of half-orbits between burn 1 and burn 3
   
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