Inertial2Rotating:

Path: AerospaceUtils/Coord

% Converts a coordinates in an inertial reference frame  to coordinates in a 
 rotating reference frame (such as the rotating coordinates typically used in 
 the circular restricted three body problem).  Both frames are 
 centered at the secondary body. The rotating coordinate system has the
 primary body fixed on the x-axis

 Since version 9.
--------------------------------------------------------------------------
   Form:
   stateOut = Inertial2Rotating(stateIn,primary,muPrimary)
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   stateIn		(6,1)    State vector in the non-rotating frame
   primary     (6,1)    State vector of the primary body
   muPrimary   (1,1)    Gravitational Parameter of the primary body

   -------
   Outputs
   -------
   stateOut    (6,1)    State vector in the rotating frame

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Children:

Math: Linear/Mag

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