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Numerical Investigation of Flapwise-Torsional Vibration Model of a Smart Section Blade with Microtab

Journal Article · · Shock and Vibration
DOI:https://doi.org/10.1155/2015/136026· OSTI ID:1212267
 [1];  [2];  [1];  [1];  [3]
  1. School of Hydraulic, Energy and Power Engineering, Yangzhou University, Yangzhou, Jiangsu 225127, China
  2. Aerospace Engineering, Embry-Riddle Aeronautical University, Daytona Beach, FL 32114-3900, USA
  3. Wright State Research Institute, AFRL RQVC, Beavercreek, OH 45431, USA
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This study presents a method to develop an aeroelastic model of a smart section blade equipped with microtab. The model is suitable for potential passive vibration control study of the blade section in classic flutter. Equations of the model are described by the nondimensional flapwise and torsional vibration modes coupled with the aerodynamic model based on the Theodorsen theory and aerodynamic effects of the microtab based on the wind tunnel experimental data. The aeroelastic model is validated using numerical data available in the literature and then utilized to analyze the microtab control capability on flutter instability case and divergence instability case. The effectiveness of the microtab is investigated with the scenarios of different output controllers and actuation deployments for both instability cases. The numerical results show that the microtab can effectively suppress both vibration modes with the appropriate choice of the output feedback controller.

Research Organization:
Univ. of Wyoming, Laramie, WY (United States)
Sponsoring Organization:
USDOE Office of Science (SC)
Grant/Contract Number:
SC0001261
OSTI ID:
1212267
Alternate ID(s):
OSTI ID: 1452905
Journal Information:
Shock and Vibration, Journal Name: Shock and Vibration Vol. 2015; ISSN 1070-9622
Publisher:
HindawiCopyright Statement
Country of Publication:
Egypt
Language:
English

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