二维翼段颤振的μ控制  

Active Flutter Suppression of a Two-dimensional Airfoil Section Using μ Synthesis

作　　者：于明礼[1] 文浩[1] 胡海岩[1] 赵永辉[1] 

机构地区：[1]南京航空航天大学振动工程研究所,江苏南京210016

出　　处：《航空学报》2007年第2期340-343,共4页Acta Aeronautica et Astronautica Sinica

基　　金：国家"863"计划(705-23)

摘　　要：采用超声电机作为作动器来实现含控制面的翼段颤振鲁棒抑制。针对作者设计的二维翼段颤振主动抑制系统,通过理论与实验相结合的方法,建立了考虑沉浮方向阻尼和作动器模型参数不确定性的控制系统模型,设计了μ控制器,并对控制器做了降阶处理。数值仿真和风洞试验表明,μ控制器可有效地抑制颤振的发生,将颤振临界速度提高23.4%。相对于H∞控制器,μ控制器的控制效果和鲁棒性更好。This paper presents how to use the ultrasonic motor as an actuator in the flutter suppression of a two-dimensional airfoil section with a control surface. The study begins with the combined theoretical and experimental modeling for the aeroservoelastic system with the damping uncertainty in plunge direction and the modeling error of the ultrasonic motor taken into consideration. Then, it focuses on the design of a controller by using μ synthesis at a given flow speed. The numerical simulations and wind tunnel tests show that the μ controller is able to suppress the flutter effectively and the critical flutter speed of controlled system is increased by 23.4%. In addition, a comparison of μ controller and H∞ controller shows that the former is superior to the latter in the flutter suppression and in the robustness with respect to the time delay in the control loop.

关 键 词：颤振主动抑制 μ控制 超声电机 风洞试验 数值仿真 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程] V215.3