FFEccH:

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   Compute the H term for the homogeneous solution to LTV diff eqs
   of relative orbit motion.

   Since version 7.
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   Form:
   H = FFEccH( nu, e, dH );
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   ------
   Inputs
   ------
   nu              (1,N)  True anomaly [rad]
   e                (1)   Eccentricity
   dH              (1,N)  Integration constant found by setting H = 0 at nu0

   -------
   Outputs
   -------
   H               (1,N)  Value of H term 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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