Path: Interplanetary/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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Interplanetary: Ephemeris/PlanetPositionEMBarycenter Common: Database/Constant Common: Graphics/Plot3D Common: Time/JD2000 Math: Linear/Mag
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