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 -------------------------------------------------------------------------- Form: [r, v] = El2RV( el, tol, mu ) -------------------------------------------------------------------------- ------ Inputs ------ 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) ------- Outputs ------- r (3,:) position vector v (3,:) velocity vector -------------------------------------------------------------------------- References: Battin, R.H., An Introduction to the Mathematics and Methods of Astrodynamics, p 128. -------------------------------------------------------------------------- See also: RV2El, RVFromKepler --------------------------------------------------------------------------
Orbit: OrbitCoord/CP2I Orbit: OrbitMechanics/M2Nu Common: General/DispWithTitle
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