Time2NuDomain:

--------------------------------------------------------------------------
   Convert a relative state from the time-domain to the nu-domain.

   This changes only the relative velocity portion (elements 4 thru 6) of
   the state vector.

   For this conversion, the velocity terms are divided by the
   time-derivative of the true anomaly (nu).

   Since version 7.
--------------------------------------------------------------------------
   Form:
   x = Time2NuDomain( x, n, e, nu )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   x               (6,1)  Relative State in time-domain, 6x1 vector, 
                           [position;velocity]
   n                (1)   Mean orbit rate [rad/s]
   e                (1)   Eccentricity
   nu               (1)   True anomaly [rad]

   -------
   Outputs
   -------
   x               (6,1)  Relative State in nu-domain, 6x1 vector, 
                           [position;velocity]

--------------------------------------------------------------------------
   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.
--------------------------------------------------------------------------

Children:

FormationFlying: Utility/NuDot