Path: Orbit/OrbitCoord
% Converts R and V to Equinoctial elements -------------------------------------------------------------------------- Form: eq = RV2Eq( r, v, mu ) -------------------------------------------------------------------------- ------ Inputs ------ r (3,1) Position vector v (3,1) Velocity vector mu Gravitational constant ------- Outputs ------- eq Elements vector [a,P1,P2,Q1,Q2,l] -------------------------------------------------------------------------- References: Bate, R.R., et. al. Fundamentals of Astrodynamics, pp. 70-71. --------------------------------------------------------------------------
Orbit: OrbitCoord/El2Eq SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/RV2El Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/Cross Math: Linear/DupVect Math: Linear/Mag
Back to the Orbit Module page