The nonlinearities present in the control surface of an aircraft can alter both the stability and per formance characteristics. The typical nonlinearities generally considered are the "saturation" and the "dead band." The present work shows that these can lead to loss of steady-state accuracy A simple formulation in terms of the eigenvalue problem is presented to predict the steady-state behavior. Analytical and numerical results for a fighter aircraft model are presented to demonstrate the utility of the methodology developed.
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