期刊
AEROSPACE SCIENCE AND TECHNOLOGY
卷 25, 期 1, 页码 242-252出版社
ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER
DOI: 10.1016/j.ast.2012.01.012
关键词
Aeroelastic instability; Model uncertainty; Subsonic compressible flow; Sliding mode control
资金
- Basic Science Research Program through the National Research Foundation of Korea [20110001145]
This paper addresses the robust aeroelastic instability suppression of an advanced aircraft wing modeled as a thin-walled beam structure with fiber-reinforced composite material featuring a circumferentially asymmetric stiffness (CAS) configuration. The unsteady aerodynamic loads in subsonic compressible flow are derived through the indicial function approach. Aeroelastic instability suppression is achieved via sliding mode control (SMC) based on sliding mode observer (SMO). To demonstrate the robustness of the SMC based on SMO, linear quadratic Gaussian (LQG) methodology is compared with respect to the model uncertainty. To this end, the obtained numerical simulation results emphasize the efficiency of the sliding mode control based on sliding mode observer to control the unstable aeroelastic phenomenon in conjunction with the model uncertainty. (C) 2012 Elsevier Masson SAS. All rights reserved.
作者
我是这篇论文的作者
点击您的名字以认领此论文并将其添加到您的个人资料中。
推荐
暂无数据