复合材料加筋结构剪切屈曲模态分析

复合材料加筋壁板逐渐应用于大型飞机机身及机翼结构，采用试验和有限元的方法研究了加筋壁板结构的剪切屈曲特性。通过剪切试验获得加筋壁板结构的屈曲载荷和破坏载荷，结果表明当结构达到屈曲状态时并不会立马丧失承载能力，屈曲载荷占破坏载荷的81.8%。对比含夹具和无夹具的剪切屈曲载荷可知，夹具对加筋板的屈曲稳定性影响较大，在进行仿真模拟时，忽略夹具可能导致严重的错误。同时，边界条件的差异会导致结构的屈曲稳定性发生改变，夹具的强弱会影响结构的传力路径，合适的边界条件可以极大地改善结构的稳定性。

Shear Buckling Mode Analysis of Composite Stiffened Structures

Composite stiffened panels have been applied to the fuselage and wing structures of large aircraft. The shear buckling characteristics of the stiffened panel structures were investigated using test and finite element methods. The buckling load and failure load of stiffened panel structure are obtained by shear test. The results show that when the structure reaches the buckling state, it will not lose its bearing capacity immediately, and the buckling load accounts for 81.8% of the failure load. Comparing the shear buckling loads with and without fixture, it can be seen that fixture have a great influence on the buckling stability of stiffened panels, and ignoring fixture may lead to serious errors in simulation. At the same time, the difference of boundary conditions may change the buckling stability of the structure, and the strength of the fixture may affect the force transmission path of the structure. Appropriate boundary conditions can greatly improve the stability of the structure.