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Shock and Vibration
Volume 2016 (2016), Article ID 5096128, 14 pages
Research Article

Stall Flutter Control of a Smart Blade Section Undergoing Asymmetric Limit Oscillations

1School of Hydraulic, Energy and Power Engineering, Yangzhou University, Yangzhou, Jiangsu 225127, China
2Aerospace Engineering Department, Embry-Riddle Aeronautical University, Daytona Beach, FL 32114-3900, USA
3Wind Energy Center, University of Wyoming, Laramie, WY 82072, USA

Received 14 November 2015; Revised 10 February 2016; Accepted 23 February 2016

Academic Editor: Gianluca Gatti

Copyright © 2016 Nailu Li et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


Stall flutter is an aeroelastic phenomenon resulting in unwanted oscillatory loads on the blade, such as wind turbine blade, helicopter rotor blade, and other flexible wing blades. Although the stall flutter and related aeroelastic control have been studied theoretically and experimentally, microtab control of asymmetric limit cycle oscillations (LCOs) in stall flutter cases has not been generally investigated. This paper presents an aeroservoelastic model to study the microtab control of the blade section undergoing moderate stall flutter and deep stall flutter separately. The effects of different dynamic stall conditions and the consequent asymmetric LCOs for both stall cases are simulated and analyzed. Then, for the design of the stall flutter controller, the potential sensor signal for the stall flutter, the microtab control capability of the stall flutter, and the control algorithm for the stall flutter are studied. The improvement and the superiority of the proposed adaptive stall flutter controller are shown by comparison with a simple stall flutter controller.