Path: Interplanetary/ThreeBody
% Simulates a spiral out from LEO with three-body dynamics. The trajectory as plotted as well as the orbital elements in the heliocentric frame. The final orbital elements at the end of the spiral out are printed to the command window. This demo demonstrates several coordinate transformation ------------------------------------------------------------------------ See also Constant, CRTBPRHS, El2RV, RV2El, TransformECIToSEMR, SEMRToSEMI, FCRTBPRHS, LowThrustCRTBP_StopFcn, Plot2D, PlotSEMTraj ------------------------------------------------------------------------ % ------------------------------------------------------------------------------- Copyright (c) 2012 Princeton Satellite Systems, Inc. All rights reserved. Since version 10. -------------------------------------------------------------------------------
Interplanetary: ThreeBody/CRTBPRHS Interplanetary: ThreeBody/FCRTBPRHS Interplanetary: ThreeBody/LowThrustCRTBP_StopFcn LunarMissions: LunarCoord/SEMRToSEMI LunarMissions: LunarCoord/TransformECIToSEMR LunarMissions: Visualization/PlotSEMTraj Orbit: OrbitCoord/El2RV Orbit: OrbitCoord/RV2El Common: Database/Constant Common: Graphics/NewFig Common: Graphics/Plot2D Common: Time/Date2JD Math: Linear/Mag Math: Linear/Unit
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