Path: Orbit/LowEnergyManeuver

% Plot the Low Energy Transfer, 3 Body Problem
 For a 3 body problem in a Non-Rotating frame as well as in a Sun-Earth
 Rotating Frame. Create two windows.
   [h,yVec,tVec] = PlotLET3BP(elements,dV1Eph,det,jDate,h);

   elements	(1,6)   Ecliptic orbital elements of the intial state
   dV1Eph    (1,1)   Magnitude of the initial burn
   det       (1,1)   Transfer time
   h         (1,2)   Optional. Figure handles to use for plots.

   h         (1,2)    Figure handles used for the plots.
   yVec      (6.:)    States in non-rotating frame
   tVec      (1,:)    Time vector


AC: ACData/ACTConstants
Orbit: LowEnergyManeuver/J20002RotPuls
Orbit: LowEnergyManeuver/Propagate3BP
SC: BasicOrbit/CP2I
SC: BasicOrbit/E2Nu
SC: BasicOrbit/El2RV
SC: BasicOrbit/M2E
SC: BasicOrbit/M2EApp
SC: BasicOrbit/M2EEl
SC: BasicOrbit/M2EHy
SC: BasicOrbit/M2Nu
SC: BasicOrbit/M2NuPb
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/DispWithTitle
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/DupVect
Math: Linear/Mag
Math: Linear/Unit

Back to the Orbit Module page