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.
   [yvec, tvec] = Propagate3BP(y,t0,tF,jDate,stmcalc)

   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
   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

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