Path: FormationFlying/Utility
% Compute the future true anomaly (unwrapped) at the specified number of orbits after the initial true anomaly. Since version 7. -------------------------------------------------------------------------- ------ Inputs ------ e (1) Eccentricity nu0 (1) Initial true anomaly [rad] nOrb (1,:) Time vector from initial true anomay [orbit periods] ------- Outputs ------- nuF (1,:) Vector of final true anomalies --------------------------------------------------------------------------
SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb 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 Math: Trigonometry/WrapPhase
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