CAJ | 학술논문

研究了高超声速飞行器壁板热颤振的非线性动力学问题。应变-位移关系基于Von-Kar-man薄板大变形理论，采用三阶活塞理论计算气动力，利用Hamilton原理建立了高超音速气流中热环境下二维壁板颤振模型。用Galerkin方法在模态空间对非线性壁板颤振方程进行离散化。运用李普诺夫理论判断受热壁板颤振的临界流速。采用数值方法在时域内求解受热壁板在高超声速气流中气动力作用下的颤振响应，分析来流速度和热效应对壁板颤振稳定性和壁板颤振边界的影响。
연구료고초성속비행기벽판열전진적비선성동역학문제。응변-위이관계기우Von-Kar-man박판대변형이론，채용삼계활새이론계산기동력，이용Hamilton원리건립료고초음속기류중열배경하이유벽판전진모형。용Galerkin방법재모태공간대비선성벽판전진방정진행리산화。운용리보낙부이론판단수열벽판전진적림계류속。채용수치방법재시역내구해수열벽판재고초성속기류중기동력작용하적전진향응，분석래류속도화열효응대벽판전진은정성화벽판전진변계적영향。
The non-linear dynamics of the hypersonic vehicles′ heat panel flutter is investigated in this pa-per. The third-order piston theory is used to compute the aerodynamic force. The strain-displacement rela-tionship based on the Von Karman sheet large deformation theory and the Hamilton principles is used to con-struct the 2D panel flutter model in the thermal environment for the hypersonic airflow. The Galerkin method is employed to make the non-linear panel flutter equation discretized in the modal space. The critical flow velocity of the heated panel flutter is analyzed with the Lipunuofu theory. The numerical method is adopted to obtain the flutter response of the heated panel when the non-linear aerodynamic force is acted upon in the time domain. The speed of the incoming flow as well as the impacts of the thermal effect on the fluttering stability and the fluttering boundary of the panel is analyzed.