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SUPPORT SITE |
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SUPPORT SITE |
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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 = 3.9860044e5)
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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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Common: General/DispWithTitle OrbitMiniToolbox: Support/CP2I OrbitMiniToolbox: Support/M2Nu
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