Path: FormationFlying/Utility
% Convert mean anomaly to true latitude. True latitude, or argument of latitude, is the angle measured between the ascending node and the orbit position vector. This quantity is useful for circular, inclined orbits where there is no periapsis from which w and M can be measured. Since version 7. -------------------------------------------------------------------------- Usage: theta = MeanAnom2TrueLat( e, w, M ); -------------------------------------------------------------------------- ------ Inputs ------ e (1) Eccentricity w (1) Argument of perigee [rad] M (1,:) Mean anomaly [rad] ------- Outputs ------- theta (1,:) True latitude [rad] --------------------------------------------------------------------------
SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb 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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