Path: Orbit/OrbitMechanics
% Generate RV from parameters v infinity and periapsis Computes hyperbolic elements from velocity at infinity, radius at periapsis Inclination, argument of periapsis and longitude of the ascending node are optional. If true anomaly is not entered a default value of 90% of the max, as computed from eccentricity, will be used. Type VInfRPToRV for a demo. -------------------------------------------------------------------------- Form: [r,v,el] = VInfRPToRV( vInf, rP, f, mu, i, lon, arg ) -------------------------------------------------------------------------- ------ Inputs ------ vInf (1,1) Velocity at infinity (km/s) rP (1,1) Radius of periapsis (km) f (1,1) True anomaly (rad) mu (1,1) Gravitational parameter (km^2/s^3) (Default earth) i (1,1) Inclination (rad) lon (1,1) Longitude of the ascending node (rad) arg (1,1) Argument of periapsis (rad) ------- Outputs ------- r (3,1) Position (km) v (3,1) Velocity (km/s) el (1,6) [a i W w e M] --------------------------------------------------------------------------
SC: BasicOrbit/El2RV SC: BasicOrbit/Nu2M Common: Database/Constant Common: General/DispWithTitle
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