skip to main content

DOE PAGESDOE PAGES

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

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.
Authors:
 [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
Publication Date:
OSTI Identifier:
1212267
Grant/Contract Number:
DESC0001261
Type:
Published Article
Journal Name:
Shock and Vibration
Additional Journal Information:
Journal Volume: 2015; Related Information: CHORUS Timestamp: 2016-07-27 14:03:26; Journal ID: ISSN 1070-9622
Publisher:
Hindawi Publishing Corporation
Sponsoring Org:
USDOE
Country of Publication:
Egypt
Language:
English