FFEccDH:

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   Compute integration constant dH for homogeneous solution to LTV diff eqs
   of relative orbit motion.

   Since version 7.
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   Form:
   dH = FFEccDH( nu0, e );
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   ------
   Inputs
   ------
   nu0             (1,N)  True anomaly (at initial state) [rad]
   e                (1)   Eccentricity

   -------
   Outputs
   -------
   dH              (1,N)  Integration constant found by setting H = 0 at nu0
                
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   References: Inalhan, Tillerson, How, "Relative Dynamics and Control of
   Spacecraft Formations in Eccentric Orbits", Journal of Guidance,
   Control & Dynamics, Vol.25, No.1, Jan-Feb 2002.
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	  Copyright 2004 Princeton Satellite Systems, Inc.
   All rights reserved.
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