Path: Orbit/LowEnergyManeuver
% Propagate a Sun-Earth-Moon 4BP with origin at the Earth-Moon barycenter.
These are dimensional equations (mks) that use the JPL planetary ephemerides.
PlanetPositionEMBarycenter must be initialized with the sun, planet, and moon,
as in
PlanetPositionEMBarycenter('initialize',[0 3 10]);
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Form:
[yvec, tvec] = Propagate4BP(y,t0,tF,jDate,stmcalc,acc)
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Inputs
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y (6,1) Current state vector [r;v]
t0 (1,1) Initial time
tF (1,1) Final time
jDate (1,1) Julian date
stmcalc (1,1) 1 if propagating the STM, 0 otherwise
acc (1,1) 1 if there is thrust, 0 if ballistic
muMoonMultiplier (1,1) 0 to 1, for the purpose of easing between 3BP and 4BP
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Outputs
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yvec (6,:) State vector
tvec (1,:) Time vector
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See also: PlanetPositionEMBarycenter, Propagate3BP
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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
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