FCRTBPRHS:

Path: Orbit/ThreeBody

% Right-hand-side for the forced circular restricted three body problem.
   The state includes mass.
     X is along primary - secondary body line
     Z is normal to plane of motion 
     Y completes right-hand system

   Since version 10.
--------------------------------------------------------------------------
   Form:
   xDot = FCRTBPRHS( x, t, mu, a, uE )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   x            (7,1)     The state vector [r;v;m]
   t            (1,1)     Time (unused)
   mu           (1,1)     Non-dimensional mass parameter.
                           Smaller mass divided by total mass of system.
   a            (3,1)     Acceleration applied to body in rotating frame
   uE           (1,1)     Exhaust velocity (non-dimensional)

   -------
   Outputs
   -------
   xDot         (7,1)     The derivative of the state vector

--------------------------------------------------------------------------

Back to the Orbit Module page