FFEccDiscreteHills:

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   Computes the relative state trajectory in an eccentric reference orbit.
   A discretized state space model of Hills equations is used, which is defined 
   by the mean orbit rate (n), eccentricity (e), and true anomaly history. 
   The "FFEccLinOrb" function is called, and the discretization is done using 
   "C2DZOH.m". 

   Since version 7.
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   Form:
   [xS,nu] = FFEccDiscreteHills( e, n, x0, nu0, aC, t )
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   ------
   Inputs
   ------
   e                  (1)    Eccentricity
   n                  (1)    Mean orbit rate (rad/sec)
   x0                (6,1)   Initial relative state
   nu0                (1)    Initial true anomaly
   aC                (3,n)   Commanded accelerations
   t                 (1,n+1) Time vector (final time corresponds to final state)

   -------
   Outputs
   -------
   xS                (6,n+1)  State trajectory of the satellite in Hill's frame

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Children:

FormationFlying: EccDynamics/FFEccLinOrb
Math: Trigonometry/UnwrapPhase
OrbitMiniToolbox: Support/M2Nu
SC: BasicOrbit/Nu2M