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.

 If there are no arguments a figure is created.
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   Form:
   [dV, theta] = ApogeeDV( eT, iT, a2, e2, i2, mu )
                 ApogeeDV( eT, iT, a2, e2, i2 );   % create plot
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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 (default Earth, km^3/sec^2)

   -------
   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:

Orbit: OrbitCoord/A2Apogee
Common: Graphics/AxesCart
Common: Graphics/Map

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