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   Test the FFEccLinOrb function. An initial reference state in the ECI frame
   is provided, along with an initial relative state in Hill's frame. 

   First, the relative state is propagated one time-step dT using FFEccLinOrb, 
   with the given acceleration in Hill's frame applied. 

   Next, we integrate the reference and secondary states in the ECI frame,
   applying the given accleration (now transformed to ECI). We then
   transform the two resulting ECI states back to the Hill's frame and
   compare.
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   Form:
   [xH_int,xH_lin] = TestFFEccLinOrb( x0, xH0, dT, aH );
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   ------
   Inputs
   ------
   x0              (6,1)  ECI position and velocity of reference 
                          [km; km/s]
   xH0             (6,1)  Hill's-frame position and velocity of relative sat
                          [km; km/s]
   dT               (1)   Time-step to integrate over [sec]
   aH              (3,1)  Acceleration to be applied (in Hill's frame)
                          [km/s/s]

   -------
   Outputs
   -------
   xH_int          (6,1)  Hill's-frame state from integrating inertial states
   xH_lin          (6,1)  Hill's-frame state from propagating linear system

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	  Copyright 2004 Princeton Satellite Systems, Inc.
    All rights reserved.
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