Path: Orbit/OrbitCoord
% Converts orbital elements to r and v for an elliptic orbit.
Type El2RV for a demo. The Keplerian elements are defined as:
* a is semi-major axis (km)
* i is inclination (rad)
* W is right ascension of the ascending node (rad)
* w is argument of perigee (rad)
* e is argument of perigee
* M is mean anomaly
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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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See also: RV2El, RVFromKepler
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Orbit: OrbitCoord/CP2I Orbit: OrbitMechanics/M2Nu Common: General/DispWithTitle
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