Path: Interplanetary/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. -------------------------------------------------------------------------- Form: [h,yVec,tVec] = PlotLET3BP(elements,dV1Eph,det,jDate,h); -------------------------------------------------------------------------- ------ Inputs ------ 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. ------- Outputs ------- h (1,2) Figure handles used for the plots. yVec (6.:) States in non-rotating frame tVec (1,:) Time vector --------------------------------------------------------------------------
Interplanetary: Ephemeris/PlanetPositionEMBarycenter Interplanetary: LowEnergyManeuver/J20002RotPuls Interplanetary: LowEnergyManeuver/Propagate3BP SC: BasicOrbit/El2RV Common: Database/Constant Common: Graphics/NewFig Math: Linear/Unit
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