期刊
AEROSPACE SCIENCE AND TECHNOLOGY
卷 10, 期 2, 页码 120-126出版社
ELSEVIER FRANCE-EDITIONS SCIENTIFIQUES MEDICALES ELSEVIER
DOI: 10.1016/j.ast.2005.10.002
关键词
robust aeroelastic control; flapped wing; Kalman filter; sliding mode observer; blast load
The performance of a robust control strategy applied to a three-degrees-of- freedom (3-DOF) flap-wing aeroelastic system impacted by a pressure pulse in the subcritical flight speed regime is investigated. The goal of its implementation is to suppress flutter instability and reduce the vibrational level in the subcritical flight speed range. To this end, the linear quadratic Gaussian (LQG) control methodology in conjunction with a sliding mode observer (SMO) are used. Comparisons with the counterpart results obtained via implementation of LQG controller with conventional Kalman filter (KF) are also provided and pertinent conclusions are outlined. (c) 2005 Elsevier SAS. All riahts 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