Path: SC/BasicOrbit
% Converts Cartesian state to Keplerian orbital elements.
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Form:
[el, E, f] = RV2El( r, v, mu )
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Inputs
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r (3,1) Position vector
v (3,1) Velocity vector
mu (1,1) Gravitational constant
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Outputs
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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
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References: Vallado, D. A. (1997.) Fundamentals of Astrodynamics and
Applications. pp. 144-147.
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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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