Path: Orbit/OrbitMechanics
% Computes the elements of an orbit with the desired synodic period. Type OrbitFromSynodic for a demo. Since version 2014.1 -------------------------------------------------------------------------- Form: el = OrbitFromSynodic( elT, p, mu, h ) -------------------------------------------------------------------------- ------ Inputs ------ el (1,6) Target orbit [a i W w e M] p (1,1) Desired synodic period mu (1,1) Gravitational constant h (1,1) Any entry get a higher orbit ------- Outputs ------- el (1,6) Orbit [a i W w e M] --------------------------------------------------------------------------
AC: ACData/ACTConstants 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 SC: BasicOrbit/Period SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/CellToMat Common: General/DeBlankLT Common: General/DeleteCell 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
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