Path: Orbit/OrbitMechanics
% Generate RV from parameters Computes hyperbolic elements from velocity at infinity, radius at perigee Inclination, argument or perigee and longitude of the ascending node are optional. 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 perigee (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 perigee (rad) ------- Outputs ------- r (3,1) Position (km) v (3,1) Velocity (km/s) el (1,6) [a i W w e M] --------------------------------------------------------------------------
AC: ACData/ACTConstants SC: BasicOrbit/CP2I SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/El2RV SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/CellToMat Common: General/DeleteCell Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/DupVect
Back to the Orbit Module page