Title

State Feedback Control of an Aeroeleastic Systems with Structural Nonlinearity

Document Type

Article

Publication Date

2003

Publication Title

Aerospace Science and Technology

Volume

7

First page number:

23

Last page number:

31

Abstract

The paper treats the question of state variable feedback control of prototypical aeroelastic wing sections with structural nonlinearity. This type of model has been traditionally used for the theoretical as well as experimental analyses of two-dimensional aeroelastic behavior. The chosen dynamic model describes the nonlinear plunge and pitch motion of a wing. A single control surface is used for the purpose of control. A control law is designed based on the state-dependent Riccati equation technique. Unlike feedback linearizing control systems reported in literature, this approach is applicable to minimum as well as nonminimum phase aeroelastic models. The closed-loop system is asymptotically stable. Simulation results are presented which show that in the closed-loop system, flutter suppression is accomplished.

Keywords

Aeroelasticity; Aeroelasticity and control; Airplanes—Wings; Feedback control systems; Flutter (Aerodynamics); Nonlinear flutter control; Nonlinear system; Suboptimal control; Nonlinear system; Suboptimal control

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

Identifier

DOI: http://dx.doi.org/10.1016/S1270-9638(02)00004-4

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