ApogeeDV:

Path: Orbit/OrbitManeuver

% Delta-V to change apogee.
   Computes the delta-v needed to go from a transfer orbit
   to a final orbit with a plane change. Assumes that the
   node line coincides with the line of apsides. 

   The default mu is km^3/sec^2.

   Since version 1.
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   Form:
   [dV, theta] = ApogeeDV( eT, iT, a2, e2, i2, mu )
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   ------
   Inputs
   ------
   eT                     eccentricity of the transfer orbit
   iT                     inclination of the transfer orbit (rad)
   a2                     semi-major axis of the final orbit
   e2                     eccentricity of the final orbit
   i2                     inclination of the final orbit (rad)
   mu                     gravitational parameter

   -------
   Outputs
   -------
   dV                     total delta v
   theta                  angle of burn with respect to the
                          final velocity vector

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   References: Kaplan, M., Modern Spacecraft Dynamics and Control, John
               Wiley & Sons, p. 91.
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Children:

Common: Graphics/AxesCart
Common: Graphics/Axis3D
Common: Graphics/NewFig
Common: Graphics/XLabelS
Common: Graphics/YLabelS
Common: Graphics/ZLabelS
Orbit: OrbitCoord/A2Apogee

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