Path: Orbit/OrbitCoord
% Converts semi-major axis, eccentricy and r to true anomaly. r and a must be in the same units. This only works for elliptical orbits. Type AERToNu for a demo. -------------------------------------------------------------------------- Form: nu = AERToNu( a, e, r ) -------------------------------------------------------------------------- ------ Inputs ------ a (1,1) Semi-major axis e (1,1) Eccentricity r (1,:) Position ------- Outputs ------- nu (1,:) True anomaly (rad) --------------------------------------------------------------------------
Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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