Sliding Mode Aeroelastic Control of Supersonic 2-D Flapped Lifting Surfaces

This paper concerns the robust linear and non-linear combined control of 2-D supersonic wing-flap aeroelastic systems using a sliding mode control (SMC). 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. Control’s effectiveness in reducing the oscillation amplitude in the subcritical flight speed range, in suppressing flutter, and in preventing the catastrophic increase of oscillatory amplitudes in the post-flutter range is demonstrated.

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