噪声与振动控制Issue(2)：44-48,5.DOI:10.3969/j.issn.1006-1335.2013.02.011
高超声速机翼颤振的LQR主动控制系统设计
Design of LQR Active Control System of Hypersonic Airfoil Flutter
摘要
Abstract
Design of an active control system based on LQR (Linear Quadratic Regulator) method for hypersonic airfoil flutter was presented. Firstly, using hypersonic two-dimensional airfoil model with cubic physical nonlinearity and aerodynamic nonlinearity, eigenvalues at the zero equilibrium point were analyzed, and a Hopf-bifurcation point was obtained. Then, an active control system based on the LQR method for hypersonic airfoil flutter analysis was designed with the given quadratic performance index of the system. The control algorithm can effectively restrain the continuous oscillation at the Hopf-bifurcation point. Furthermore, it is simple and easy to realize in engineering. Finally, the efficiency of this control method was verified by simulation results.关键词
振动与波/高超声速/机翼颤振/主动控制/Hopf分叉/LQRKey words
vibration and wave/hypersonic/airfoil flutter/active control/Hopf-bifurcation/LQR分类
信息技术与安全科学引用本文复制引用
王璐,王玉惠,吴庆宪,姜长生..高超声速机翼颤振的LQR主动控制系统设计[J].噪声与振动控制,2013,(2):44-48,5.基金项目
国家自然科学基金(11102080)；中央高校基本科研业务费专项资金资助(NP2011049；NZ2012005) （11102080）
