Path: Orbit/OrbitCoord
% Computes true anomaly from semi-major axis, eccentricity and radius. a and r must be in the same units. Type RToNu for a demo of an elliptic orbit. -------------------------------------------------------------------------- Form: nu = RToNu( a, e, r ) -------------------------------------------------------------------------- ------ Inputs ------ a (1,1) Semi-major axis e (1,1) Eccentricity r (1,:) Radius ------- Outputs ------- nu (1,:) True anomaly (rad) --------------------------------------------------------------------------
Orbit: OrbitCoord/SLR Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/CP2I SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/Axis3D Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Math: Linear/DupVect Math: Linear/Mag
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