Abstract

This paper presents a comparative analysis of control strategies applied to a nonlinear 2-D wing-flap system operating in supersonic/hypersonic flight speed regimes. Open and closed-loop aeroelastic response and flutter of 2-D supersonic lifting surfaces are investigated. In this context, the implications of aerodynamic and structural nonlinearities on the aeroelastic response in the post-flutter range are presented and various robust control methodologies, such as sliding mode control, H∞ and fuzzy logic control, are compared. The controls’ effectiveness in reducing the aeroelastic vibrations in the various flight speed ranges and in suppressing flutter is demonstrated.

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