An Elementary Explanation of the Flutter Mechanism with Active Feedback Controls

Published

Journal Article

An elementary explanation of wing flutter suppression problems with active feedack control is made using a standard root locus technique. The object of the study is to obtain insight into the control of converging frequency flutter such as the classical bending-torsion flutter of a wing. The model analyzed is a twodimensional, typical section airfoil with pure gain feedback of the main wing motion. In this simple system, stability boundary solutions are expressed in a closed form and valuable information is obtained for various kinds of feedback signals. The results for an exploratory example are discussed. The analysis of this example using Nissim's energy method is also attempted. © 1979 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.

Full Text

Duke Authors

Cited Authors

  • Horikawa, H; Dowell, EH

Published Date

  • January 1, 1979

Published In

Volume / Issue

  • 16 / 4

Start / End Page

  • 225 - 232

International Standard Serial Number (ISSN)

  • 0021-8669

Digital Object Identifier (DOI)

  • 10.2514/3.58509

Citation Source

  • Scopus