DVHohE:

Path: Orbit/OrbitManeuver

% Computes two impulses needed to transfer between two elliptical coplanar orbits.
   Transfers from periapsis of 1 to apoapsis of 2.

   Since version 1.
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   Form:
   [dv, dv1, dv2, et, at] = DVHohE( e1, a1, e2, a2, mu )
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   Inputs
   ------
   e1                     Eccentricity of first orbit
   a1                     Semi-major axis of first orbit
   e2                     Eccentricity of final orbit
   a2                     Semi-major axis of final orbit
   mu                     Gravitational parameter

   -------
   Outputs
   -------
   dv                     Total delta v
   dv1                    Low orbit to transfer orbit delta v
   dv2                    Transfer orbit to high orbit delta v
   et                     Transfer orbit eccentricity
   at                     Transfer orbit semimajor axis

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   References: Kaplan, M., Modern Spacecraft Dynamics and Control, John
               Wiley, pp. 87-88.
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Children:

Orbit: OrbitCoord/A2Apogee
Orbit: OrbitCoord/A2Perige
Common: General/DeBlankLT
Common: Graphics/Mesh2
Common: Graphics/NewFig
Common: Graphics/PltStyle
Common: Graphics/XLabelS
Common: Graphics/YLabelS
Common: Graphics/ZLabelS
Math: Linear/DupVect

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