FRotatingLagrange:

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   Sail orbit RHS in a 3 body dimensionless rotating frame.
   The sail normal is always directed along the Sun-line. The state is the
   perturbation from the Lagrange point. This is a linearization.
   See also LunarHalo.

   Since version 7.
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   Form:
   xDot = FRotatingLagrange( t, s, d )
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   ------
   Inputs
   ------
   t                (1,1) Time
   s                (6,1) State [x;y;z;dx/dt;dy/dt;dz/dt]
   d                 (:)  Structure
     theta   (1,1) Sail control angle
     accel   (1,1) Sail acceleration
     xL      (1,1) Coordinate of Lagrange point in corotating frame
     wS      (1,1) Rate of rotation of the sun vector
     mu      (1,1) System gravity parameter, m2/(m1+m2)
     control (1,1) Control flag
     r0      (1,3) Desired offsets
     linear  (1,1) Flag for linearized form

   -------
   Outputs
   -------
   xDot             (6,1) state derivative

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   Reference: Colin R. McInnes, "Solar Sailing: Technology, Dynamics and Mission
              Applications", Springer Praxis, London, 1999.
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Children:

Math: Linear/Mag