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

Published

Journal Article

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%.

Full Text

Duke Authors

Cited Authors

  • Vipperman, JS; Clark, RL; Conner, M; Dowell, EH

Published Date

  • January 1, 1998

Published In

Volume / Issue

  • 35 / 2

Start / End Page

  • 224 - 229

International Standard Serial Number (ISSN)

  • 0021-8669

Digital Object Identifier (DOI)

  • 10.2514/2.2312

Citation Source

  • Scopus