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Experimental active control of a typical section using a trailing-edge flap

Vipperman, JS and Clark, RL and Conner, M and Dowell, EH (1998) Experimental active control of a typical section using a trailing-edge flap. Journal of Aircraft, 35 (2). 224 - 229. ISSN 0021-8669

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Abstract

This paper presents an experimental implementation of an active control system used to suppress flutter in a typical section airfoil. The H2 optimal control system design is based on experimental system identifications of the transfer functions between three measured system variables - pitch, plunge, and flap position - and a single control signal that commands the flap of the airfoil. Closed-loop response of the airfoil demonstrated gust alleviation below the open-loop flutter boundary. In addition, the flutter boundary was extended by 12.4% through the application of active control. Cursory robustness tests demonstrate stable control for variations in flow speed of ± 10%.


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Details

Item Type: Article
Status: Published
Creators/Authors:
CreatorsEmailPitt UsernameORCID
Vipperman, JSjsv@pitt.eduJSV0000-0001-5585-954X
Clark, RL
Conner, M
Dowell, EH
Date: 1 January 1998
Date Type: Publication
Journal or Publication Title: Journal of Aircraft
Volume: 35
Number: 2
Page Range: 224 - 229
DOI or Unique Handle: 10.2514/2.2312
Schools and Programs: Swanson School of Engineering > Mechanical Engineering and Materials Science
Refereed: Yes
ISSN: 0021-8669
Date Deposited: 21 Sep 2018 19:13
Last Modified: 02 Feb 2019 15:55
URI: http://d-scholarship.pitt.edu/id/eprint/35333

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