Sliding Mode Robust Control of Supersonic Three Degrees-of-Freedom Airfoils

被引：11
|
作者：
Lee, Bok-Hee [1 ]
Choo, Jeong-hwan [1 ]
Na, Sungsoo [1 ]
Marzocca, Piergiovanni [2 ]
Librescu, Liviu [3 ]
机构：
[1] Korea Univ, Dept Mech Engn, Seoul 136701, South Korea
[2] Clarkson Univ, Dept Mech & Aeronaut Engn, Potsdam, NY 13699 USA
[3] Virginia Polytech & State Univ, Dept Engn & Mech, Blacksburg, VA 24061 USA
来源：
INTERNATIONAL JOURNAL OF CONTROL AUTOMATION AND SYSTEMS | 2010年 / 8卷 / 02期
关键词：
Aeroelasticity; 3DOF airfoil system; sliding mode control; sliding mode observer; ACTIVE CONTROL TECHNOLOGY; AEROELASTIC CONTROL;
D O I：
10.1007/s12555-010-0214-8
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
The robust aeroelastic control of a three-degrees-of-freedom (3DOF) linear and non-linear wing-flap system under sliding mode control (SMC) and operation in supersonic flight speeds is presented. Open- and closed-loop aeroelastic responses to blast and sonic-boom excitation in the wing-flap system with uncertainty, as well as flutter analysis, are investigated along with the implementation of a Sliding Mode Observer (SMO). The effectiveness of control in reducing the amplitude of oscillation and preventing flutter instability is demonstrated.
引用
收藏
页码：279 / 288
页数：10
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