结构非线性机翼的超音速和高超音速颤振  

Flutter of Airfoil with Structural Nonlinearity in Supersonic and Hypersonic Flow

作　　者：郑国勇[1] 杨翊仁[1] 

机构地区：[1]西南交通大学应用力学与工程系,四川成都610031

出　　处：《西南交通大学学报》2007年第5期578-582,共5页Journal of Southwest Jiaotong University

基　　金：国家自然科学基金委与中国工程物理研究院联合资助项目(10576024)

摘　　要：为探讨超音速、高超音速流中二元机翼的气动弹性特性,基于活塞理论计算了作用在翼面上的气动力,运用能量方法建立了系统的运动微分方程,采用Hopf分叉理论确定了系统的临界颤振速度,并考查了系统参数对临界颤振速度的影响;采用等效线性化和数值积分法研究了具有立方非线性刚度系统的极限环响应,二者结果一致.结果表明,在一定的(无量纲)速度范围内(9.48<v<43.25),系统产生极限环响应;随流体速度增大,系统的极限环幅值增大.In order to investigate the aeroelastic characteristics of a two-dimensional airfoil in supersonic and hypersonic flow, aerodynamic force on an airfoil was calculated based on the piston theory, and the governing equations were established by using the energy method. The critical flutter velocity was obtained by using the Hopf bifurcation theory, and the effects of system parameters on the critical flutter velocity were discussed. In addition, limit cycle responses were investigated using the equivalent linearity method and the numerical integration algorithm, the same results being obtained. The research results show that the limit cycle response occurs when non-dimensional flow velocity ranges from 9.48 to 43.2, and the amplitude of limit cycle increases with increasing of flow velocity.

关 键 词：活塞理论 马赫数 高超音速 极限环颤振 机翼 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程] O322[理学—一般力学与力学基础]