Path: Orbit/LowEnergyManeuver
% Propagate a Sun-Earth 3BP with origin at the Earth system barycenter. These are dimensional equations (mks) that use the JPL planetary ephemerides. PlanetPositionEMBarycenter must be initialized with the sun as the first body. Type Propagate3BP for a demo. -------------------------------------------------------------------------- Form: [yvec, tvec] = Propagate3BP(y,t0,tF,jDate,stmcalc) -------------------------------------------------------------------------- ------ Inputs ------ y (6,1) Current state vector [r;v] (km;km/s) t0 (1,1) Initial time (s) tF (1,1) Final time (s) jDate (1,1) Julian date stmcalc (1,1) true if propagating the STM, false otherwise ------- Outputs ------- yvec (6,:) State vector tvec (1,:) Time vector --------------------------------------------------------------------------
AC: ACData/ACTConstants SC: BasicOrbit/RVFromKepler SC: Ephem/CEcl2Eq SC: Ephem/InterpolateState SC: Ephem/PlanetPosJPL SC: Ephem/PlanetPositionEMBarycenter SC: SCData/bin2000 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 Common: Time/JD2000 Math: Linear/Mag
Back to the Orbit Module page