Abstract
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 surface control methods is compared to the results obtained using piezoelectric actuators on the skins of the wing. 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.
Sensors and Control Interface Methods Based on Triboelectric Nanogenerator in IoT Applications
