Kms2CRTBP:

Path: Orbit/OrbitCoord

% Transform from km and sec to Jacobi coordinates for circular restricted
 Transforms a state vector from units associated with Jacobi coordinates of the
 Circular Restricted Three Body Problem to units of km and sec
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   Form:
   [stateOut,mu,sec2tu] = Kms2CRTBP(stateIn,distanceUnit,muPrimary,muSecondary);
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   ------
   Inputs
   ------
   stateIn        (1,6)  Initial state vector 
   distanceUnit    (1)   Distance from the Primary to the Secondary
   muPrimary       (1)   Gravitational Parameter of the Primary
   muSecondary     (1)   Gravitational Parameter of the Secondary

   -------
   Outputs
   -------
   stateOut         (1,6) 	  Output state vector
   mu                (1)     Gravitational Parameter of the CRTBP
   sec2tu            (1)     Scaling factor for time
  
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