RV2El:

Path: SC/BasicOrbit

% Converts Cartesian state to Keplerian orbital elements.
--------------------------------------------------------------------------
   Form:
   [el, E, f] = RV2El( r, v, mu )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   r               (3,1) Position vector
   v               (3,1) Velocity vector
   mu              (1,1) Gravitational constant

   -------
   Outputs
   -------
   el              (1,6) Elements vector [a,i,W,w,e,M]
   E               (1,1) Eccentric anomaly
   f               (1,1) True anomaly

   See also: El2RV, RVFromKepler

--------------------------------------------------------------------------
   References:   Vallado, D. A. (1997.) Fundamentals of Astrodynamics and
                 Applications. pp. 144-147.
--------------------------------------------------------------------------

Children:

SC: BasicOrbit/E2M
SC: BasicOrbit/Nu2E
SC: BasicOrbit/Nu2M
Common: CommonData/SwooshWatermark
Common: General/CellToMat
Common: General/MatToCell
Common: General/Watermark
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/PltStyle
Math: Linear/Cross
Math: Linear/DupVect
Math: Linear/Mag

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