Variable Structure Flutter Control of a Prototypical Wing Section with Unsteady Aerodynamics

Authors

Shaun Chemplavil, University of Nevada, Las Vegas
Sahjendra N. Singh, University of Nevada, Las VegasFollow
William R. Wells, University of Nevada, Las VegasFollow

Document Type

Article

Publication Date

2004

Publication Title

Systems Science

Volume

30

Issue

2

First page number:

111

Last page number:

118

Abstract

This paper presents a variable structure control system for the realization of an aeroelastic system with unsteady aerodynamics. The aeroelastic model describes the plunge and pitch motion of a wing. Based on the sliding mode design technique, a control law for the trajectory control of the pitch angle is derived. For the synthesis of the controller, only the plunge displacement, pitch angle, control surface deflection and their derivatives are measured, and the states associated with Theodorsen’s function are treated as unknown signals. In the closed-loop system, the state vector asymptotically convergers to the origin.

Keywords

Aeroelasticity; Airplanes—Wings; Intelligent control systems; Nonlinear systems; Sliding mode control; Structural control (Engineering); Unsteady flow (Aerodynamics)

Permissions

Use Find in Your Library, contact the author, or use interlibrary loan to garner a copy of the article. Publisher copyright policy allows author to archive post-print (author’s final manuscript). When post-print is available or publisher policy changes, the article will be deposited

Repository Citation

Chemplavil, S., Singh, S. N., Wells, W. R. (2004). Variable Structure Flutter Control of a Prototypical Wing Section with Unsteady Aerodynamics. Systems Science, 30(2), 111-118.