高超音速流中双楔形翼段的颤振分析及PID控制  

FlutterAnalysis and PID Control of Double-wedge Airfoil in Hypersonic Flow

作　　者：冯军楠 王立峰[1] 

机构地区：[1]南京航空航天大学机械结构力学及控制国家重点实验室,南京210016

出　　处：《科学技术与工程》2014年第14期284-288,293,共6页Science Technology and Engineering

摘　　要：在高超音速流中,气动力和惯性力的耦合作用可能导致机翼发生颤振。应用三阶活塞理论计算非定常气动力,建立双楔形翼段的运动微分方程;并采用Runge-Kutta法求解翼段的运动微分方程,得到翼段的时间历程及相轨迹线。设计一种PID控制器,可以通过改变控制面角度来抑制翼段的颤振运动。结果表明,PID控制能够有效地抑制机翼的颤振,使系统运动迅速趋于稳定。In hypersonic flow, coupling between aerodynamic and inertial force may make the airfoil flutter. The third order piston theory is used to estimate the unsteady aerodynamic loads to establish differential equations of the double-wedge airfoil. It is solved based on the Runge-Kutta method to get time history and phase trajectories of system. PID controller is designed to suppress the flutter of the airfoil by changing the angle of control surface. The results show that PID controller can effectively suppress the airfoil flutter and stablized system quickly.

关 键 词：双楔形翼段 颤振 活塞理论 Runge—Kutta法 PID控制 

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]