WIND-TUNNEL AEROELASTIC RESPONSE OF PIEZOELECTRIC AND AILERON CONTROLLED 3-D WING

摘要

This paper presents the results of wind tunnel testing performed on a true three dimensional adaptive wing structure. The focus of this study was to test the aeroelastic response and control of a wing built with conventional stressed skins. The aeroelastic performance of the wing using traditional aerodynamic control surface methods is compared to the results obtained using piezoelectric actuators bonded to the skins of the wing. Smaller piezoelectric sensors also bonded to the wing are used to provide feedback for the control law. Results are presented for the system identification, free stream vibration and buffeting tests performed in the wind tunnel. The design of the adaptive wing and control interface is discussed in addition to the experimental setup and a discussion of the results.