PropagateCRTBP:

Path: Orbit/ThreeBody

% Propagate an arbitrary CRTBP with origin at the secondary body.
   The default bodies are the earth and sun. It can propagate
   just the dynamical equations or the state transition matrix.

   This is a special case of the general three-body problem where
   the primary and secondary bodies move in circular orbits about
   the common center of mass, and the effect of the gravitational
   attraction of the smallest body is ignored.

   Propagation is done using ode113.

   Since version 9.
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   Form:
   [tvec, yvec] = PropagateCRTBP(y0,t0,tF,mu,stmcalc)
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   ------
   Inputs
   ------
   y0             (6,1)    Current state vector [r;v]
   t0             (1,1)	Initial time
   tF             (1,1)	Final time
   mu             (1,1)	CRTBP mass parameter
   stmcalc        (1,1)	1 if propagating the STM, 0 otherwise

   -------
   Outputs
   -------
   t               (1,:)	Time vector
   y               (6,:) 	State vector

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