DiscreteGVE:

--------------------------------------------------------------------------
   Computes the relative state trajectory in an eccentric reference orbit.
   A discretized state space model of Gauss' variational equations is used, 
   which is defined by the reference orbital elements.
   The "GVEDynamics" function is called to get the continuous matrices, 
   and the discretization is done using "C2DZOH.m". 

   Since version 7.
--------------------------------------------------------------------------
   Form:
   [dEl,M] = DiscreteGVE( el, dEl0, aC, t )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   el                (1,6)   Reference orbital elements [a,i,W,w,e,M]
   dEl0              (1,6)   Initial relative state
   aC                (3,n)   Commanded accelerations [km/s/s]
   t                (1,n+1)  Time vector (final time corresponds to final state)

   -------
   Outputs
   -------
   dEl              (n+1,6)  State trajectory of the satellite in Hill's frame
   M                (n+1,1)  Mean anomaly over time t

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

Children:

Common: Control/C2DZOH
Orbit: OrbitMechanics/GVEDynamics
SC: BasicOrbit/OrbRate
SC: BasicOrbit/Period