AFLTSpiral:

Path: Orbit/OrbitMechanics

% Low thrust delta v between two circular orbits. 
   The acceleration is aligned with the velocity vector. Computes the final apogee

   Since version 2.
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   Form:
   [aF, dVRatio, t] = AFLTSpiral( a0, dV, accel, mu )
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   ------
   Inputs
   ------
   a0                 Initial semi-major axis
   dV         (:)     Total delta-v
   accel              acceleration
   mu                 Gravitational parameter

   -------
   Outputs
   -------
   aF         (:)     Final semi-major axis
   dVRatio    (:)     Ratio of total delta-v to Hohmann Delta-V
   t                  Maneuver duration (days)

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   References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
               pp. 89-90.
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Children:

Orbit: OrbitManeuver/DVHoh
Common: Graphics/Plot2D

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