This paper presents the results of wind tunnel testing performed on a three-dimensional adaptive wing structure. The focus of this study was to test the aeroelastic response and control of a wing built with adaptive 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.
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References
1.
1. Suleman, A., Moniz, P.A. and Costa, A.P. (1999). Experimental flutter and buffeting suppression using piezoelectric actuators and sensors. ASME Adaptive Structures and Material Systems Conference, AD-Vol. 59/MD-Vol. 87. pp. 293-299.
2.
2. Suleman, A., Moniz, P.A. and Costa, A.P. (1999). Modeling of adaptive composite structures and application to aircraft structures. In: Proceedings of European Conference on Computational Mechanics. Munich, Germany. August.
3.
3. Crawley, E.F. and de Luis, J. (1987). Use of piezoelectric actuators as elements of intelligent structures. AIAA Journal, 25: 1373-1385.
4.
4. Heeg, J., Miller, J.M. and Doggett, R.V. (1993). Attenuation of empennage buffet response through active control of damping using piezoelectric material. NASA TM-107736.
5.
5. McGowan, A.R., Heeg, J. and Lake, R.C. (1996). Results of wind-tunnel testing from the piezoelectric aeroelastic response tailoring investigation. AIAA-96-1511-CP, NASA Langley Research Center, Hampton Virginia.
6.
6. Busan, R. (1998). Flutter model technology. WL-TR-97-3074, Wright-Patterson Air Force Base, OH45433-47542.
7.
7. Active Control experts ACX Inc. (1997). Quickpack Piezoelectric Actuators. Sales Catalogue, Cambridge, MA, USA.
