NuDot:

--------------------------------------------------------------------------
   Compute the time-derivative of the true anomaly.

   Since version 7.
--------------------------------------------------------------------------
   Form:
   [nuDot,nuDotDot] = NuDot( n, e, nu );
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   n                (1)   Mean orbit rate [rad/s]
   e                (1)   Eccentricity
   nu              (1,N)  True anomaly [rad]

   -------
   Outputs
   -------
   nuDot           (1,N)  Time-derivative of true anomaly [rad/s]
   nuDotDot        (1,N)  Second Time-derivative of true anomaly [rad/s/s]

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