Propagate4BP:

Path: Orbit/OrbitSim

% Propagate a Sun-Earth-Moon 4BP with origin at the Earth-Moon barycenter 

   Since version 9.
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   Form:
   [yvec, tvec] = Propagate4BP(y,t0,tF,stmcalc);
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   ------
   Inputs
   ------
   y              (6,1)    current state vector [r;v]
   t0             (1)      initial time
   tF             (1)      final time
   stmcalc        (1)      1 if propagating the STM, 0 otherwise

   -------
   Outputs
   -------
   yvec           (6,:) 	State vector
   tvec           (:)      Time vector
  
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Children:

Common: Database/Constant
Math: Linear/Mag
SC: Ephem/PlanetPositionEMBarycenter

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