FlybyHyperbola:

Path: Orbit/OrbitMechanics

% Compute the required orbital elements for a flyby
--------------------------------------------------------------------------
   Form:
   b = FlybyHyperbola( r, v, rP, mu )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   r   (1,1)   Distance
   v   (1,1)   Velocity
   rP	(1,:)   Perigee
   mu	(1,1)   Mu
   
                        
   -------
   Outputs
   -------
   b   (1,1)	Datastructure
             .a  (1,1) semimajor axis
           	.e  (1,1) eccentricity
           	.rP (1,1) perigee
            	.vP (1,1) perigee velocity
            	.t  (1,1) Time to r
            	.h  (1,1) Hyperbolic anomaly at r
                        
--------------------------------------------------------------------------

Children:

SC: BasicOrbit/RV2A
SC: BasicOrbit/VOrbit
Common: CommonData/SwooshWatermark
Common: General/CellToMat
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle
Common: Graphics/TimeLabl

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