复合材料波纹板剪切载荷作用下的屈曲试验与分析

复合材料波纹板稳定性是飞机机翼结构设计需要考虑的重要方面,是目前飞机结构设计中的一大难点.为了建立波纹板屈曲的数值分析方法,对复合材料波纹板在剪切载荷作用下的屈曲进行试验、工程算法和有限元方法研究.通过试验,探索了3种不同波长的复合材料波纹板的屈曲载荷和破坏载荷；采用工程算法和有限元方法计算了8种不同波长的复合材料波纹...

Buckling Investigation of Composite Corrugated PanelSubject to Shear Loads

It is of great significance and difficulty to ensure the stability of the composite corrugated panels in the design of aircraft wing structures. The main purpose of this paper is to establish a numerical method for the buckling of composite corrugated panel under shear loads via experiments and computations. The buckling and failure loads are examined by experiments for corrugated panels with three different wave lengths. Then, the buckling loads for eight different wave lengths are explored by the engineering method and the finite element method and are compared with experimental data. Finally the correction factors for the computational buckling loads are proposed. Results reveal that compared with experimental data, the buckling loads are greater than the experimental loads with the engineering method, while smaller with the finite element method. The results also show the longer the wave length is, the bigger the error is for the computational buckling loads. In addition, the results show that the computational buckling loads can be approximated to experimental loads by the proposed correction factors, which means that the correction factors are feasible and efficient.