Path: FormationFlying/Utility
% 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. --------------------------------------------------------------------------
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