Path: SC/BasicOrbit
% Converts orbital elements to r and v for an elliptic orbit.
Type El2RV for a demo.
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Form:
[r, v] = El2RV( el, tol, mu )
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Inputs
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el (:,6) Elements vector [a,i,W,w,e,M] (angles in radians)
tol (1,1)* Tolerance for Kepler's equation solver. (default = 1e-14)
mu (1,1)* Gravitational constant. (default = 3.98600436e5)
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Outputs
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r (3,:) position vector
v (3,:) velocity vector
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References: Battin, R.H., An Introduction to the Mathematics and
Methods of Astrodynamics, p 128.
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SC: BasicOrbit/CP2I SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/DupVect
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