摘要
分析了大攻角超声速翼面气动加热条件下的热颤振。根据模态叠加法建立颤振运动方程,用当地流活塞及小扰动线性化理论分别计算超声速区和亚声速区的非定常气动力,状态空间法与Runge-Kutta法结合仿真求解结构动响应。给出的两个工程实例计算结果表明,该方法计算精度可满足工程要求。另外还讨论了气动加热效应对颤振的影响。
The thermo-flutter of supersonic wing with high angle of attack under the condition of aerodynamic heating was analyzed in this paper. The flutter motion equation was founded by modal superposition method, The unsteady aerodynamic forces in the supersonic and subsonic field were calculated respectively by the methods of local flow piston theory and the linearization theory of small disturbance. And the motion response was solved by state space method and Runge-Kutta method. The computation results of the two examples showed that the accuracy of the method met the requirement in engineering. Meanwhile, the impact of aerodynamics heating on flutter was discussed.
出处
《上海航天》
北大核心
2006年第4期30-33,共4页
Aerospace Shanghai
关键词
气动热弹性
超声速流
大攻角翼面
颤振
热颤振
Aemthermoelasticity
Supersonic flow
High angle of attack wing
Flutter
Thermo-flutter
