NuDot:

Path: FormationFlying/Utility

% Compute the time-derivative of the true anomaly.

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

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