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]);
   [yvec, tvec] = Propagate4BP(y,t0,tF,jDate,stmcalc,acc)

   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

   yvec      (6,:) State vector
   tvec      (1,:) Time vector
  See also: PlanetPositionEMBarycenter, Propagate3BP


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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