Path: SC/BasicOrbit
% Computes m, nu and E from r, a and e. Type RAEToM for a demo -------------------------------------------------------------------------- Form: [m, nu, E] = RAEToM( r, a, e ) -------------------------------------------------------------------------- ------ Inputs ------ r (1,1) Orbit radius a (1,1) Orbit semi-major axis e (1,1) Orbit eccentricity ------- Outputs ------- m (1,1) Mean anomaly (rad) nu (1,1) True anomaly (rad) E (1,1) Eccentrci anomaly (rad); --------------------------------------------------------------------------
SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Math: Linear/DupVect
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