FFEccRMat:

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   Compute the state-transition matrix, R, given the eccentricity and true anomaly.
       xH = R*D
   where D is the vector of integration constants found from initial conditions.

   Since version 7.
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   Form:
   R      = FFEccRMat( nu, e, dH );
   [R,dH] = FFEccRMat( nu, e );
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   ------
   Inputs
   ------
   nu              (1,N)  True anomaly [rad]
   e                (1)   Eccentricity
   dH               (1)   Integration constant found by setting H = 0 at nu0
                          (Optional. If not provided, it will be computed
                          using the first nu supplied)

   -------
   Outputs
   -------
   R             (6*N,6)  Transformation matrix for equation xH = R*D
                          where D is the integration constant vector.

   dH               (1)   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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