Path: Orbit/Interplanetary
% Generate elements and orbit state for the asteroid Apophis. Utilizes an ephemeris point from 2009. -------------------------------------------------------------------------- Form: [elA, rA, vA, jD] = ApophisOrbit -------------------------------------------------------------------------- ------ Inputs ------ None ------- Outputs ------- elA (1,6) [a i Omega omega e M] rA (3,1) Heliocentric position (km) vA (3,1) Heliocentric velocity (km) jD (1,1) Julian day number of epoch --------------------------------------------------------------------------
AC: ACData/ACTConstants SC: BasicOrbit/E2M SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: BasicOrbit/RV2El SC: BasicOrbit/RVFromKepler 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/NewFig Common: Graphics/Plot2D Common: Graphics/Plot3D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Time/DTSToDTA Common: Time/Date2JD Math: Linear/Cross Math: Linear/DupVect Math: Linear/Mag
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