高速流场中变刚度复合材料层合板颤振分析

变刚度复合材料层合板在高速流场中的颤振行为是设计中需要考虑的问题。本文研究了高速流场中的曲线纤维变刚度层合复合材料壁板非线性颤振响应，分析了边界条件和纤维方向对颤振特性的影响。利用von-Karman大变形应变-位移关系，采用气动力活塞理论，根据虚功原理和有限元法建立变刚度复合材料壁板颤振的气动弹性力学模型，采用Newmark法对壁板的颤振方程求解。给出了不同边界条件和纤维方向条件下层合复合材料壁板的颤振特性。计算结果表明：随着纤维在板中心处或在边界±a/2处与x方向夹角（T₀或T₁）的增大，颤振临界动压减小；相同动压下，随着T₀或T₁的增大，极限环振幅增大。研究表明采用曲线纤维进一步提高了复合材料层合板的可设计性，通过调整曲线纤维路径可以改变复合材料壁板的颤振特性。

Panel flutter of variable stiffness composite laminates in supersonic flow

Panel flutter behaviour of variable stiffness laminates in high supersonic flow is of great interest in design. The nonlinear flutter behaviour of variable stiffness composite laminates with curvilinear fibers in high supersonic flow is investigated, and effects of boundary condition and ply orientation are studied. The classical lamination theory along with the von-Karman large deflection strain-displacement relationship is used for structural modeling, and the linear piston theory is used for aerodynamic modeling. The aeroelastic model of panel flutter is established based on the principle of virtual work and the finite element method, which is then solved by Newmark method. The flutter behavior under different boundary conditions and ply orientation are obtained. The results show that the critical dynamic pressure decreases as the path orientations in the center and vertical edges of a plate (T₀ or T₁) increases, and the limit cycle amplitude increases as T₀ or T₁ increases under the same dynamic pressure. It also turns out that the designability of composite laminates can be improved by using curvilinear fibers, the flutter behaviour of variable stiffness composite laminates can be changed by varying the fiber orientation.