ChangePerigee:

Path: Orbit/OrbitManeuver

% Compute the delta V required to change perigee
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   Form:
   b = ChangePerigee( d )
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   ------
   Inputs
   ------
   d			  (:)     Input data structure
                         .a   (1,1)   Semi-major axis
                         .e   (1,1)   Eccentricity of initial orbit
                         .rP  (1,:)   New Perigee
                         .mu  (1,1)   Mu
   
                        
   -------
   Outputs
   -------
   b             (:)     Output data structure
                         .dV  (1,:)   Datastructure
                         .e   (1,:)   New eccentricity
                         .a   (1,:)   New semi-major axis
                         .vA  (1,:)   Apogee velocity
                        
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Children:

Common: Graphics/Plot2D

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