摘要
超声速飞行器外表具有大量的蒙皮壁板结构,其在巡航过程中会受到气动、热、声及机械等载荷的联合作用.本文针对超声速气流中的复合材料壁板结构,基于一阶剪切变形理论(First-Order Shear Deformation Theory,FSDT)和超声速活塞理论,推导得到了复合材料壁板的气热弹动力学的能量泛函,并运用Hamilton原理变分求得系统的控制方程,利用牛顿迭代法结合Newmark法,求解获得了壁板的临界颤振动压和时域动力学响应.通过变参数计算,分析了不同参数对于壁板动力学响应的影响.最后,应用非线性能量阱(Nonlinear Energy Sink,NES)对复合材料壁板的动力学响应进行颤振控制,结果表明,NES可以有效降低壁板的颤振极限环振幅,从而极大提高超声速飞行器的可靠性和寿命.
The plate structures are the basic elements in the flight vehicle,and they are exposed in severe environment during the cruise with aerodynamic,thermal and mechanical loads acted on them.In this paper,the first order deforma⁃tion plate theory and supersonic piston theory were employed to formulate the energy functionals of the composite plate in supersonic airflow.The governing equations of the system were obtained by using the Hamilton’s principle,and the dy⁃namic responses of the plate were computed by adopting the Newmark method and Newton iteration method.The influ⁃ence of key parameters on the dynamic behaviors of the composite plate was discussed.Finally,the vibration control of the plate was carried out by using the nonlinear energy sink,and the results showed that the dynamic responses can be suppressed by the nonlinear energy sink.
作者
周凯
倪臻
黄修长
华宏星
Zhou Kai;Ni Zhen;Huang Xiuchang;Hua Hongxing(Institute of Vibration,Shock and Noise,State Key Laboratory of Mechanical System and Vibration,Collaborative Innova-tion Center for Advanced Ship and Deep-Sea Exploration,Shanghai Jiao Tong University,Dongchuan Road 800,Shang-hai,200240,China)
出处
《动力学与控制学报》
2020年第6期67-76,共10页
Journal of Dynamics and Control
基金
国家重大基础研究项目(111402028)。
