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Analysis of the Steady State Effects of the Control Surface Nonlinearities on the Performance of a Fighter Aircraft

School of Aerospace and Mechanical Engineering, University College, University of New South Wales, Canberra, Australia

Subodh Kumar Nayak

Department of Aerospace Engineering, Indian Institute of Technology, Mumbai, India

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.

Key Words: Nonlinearities • flight control system • steady-state accuracy • eigenvalues

Journal of Vibration and Control, Vol. 6, No. 6, 923-935 (2000)
DOI: 10.1177/107754630000600606


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