This article presents a theoretical formulation presented for conducting a buckling analysis of the composite sandwich plate with multiple holes via the homogenization method. The validity of the theoretical formulation was verified by comparing the results of the finite element analysis and experimental analysis. Finally, the theoretical formulation was used to optimize a composite sandwich plate with multiple holes for the design of an aircraft structure to minimize the mass. The optimization result allows a database to be obtained on the buckling characteristics of composite sandwich structures with multiple holes for applying aerospace applications. We then concluded that the theoretical formulation is well-suited to buckling analysis of a composite sandwich structure with multiple holes for aerospace applications due to their relative simplicity and computational efficiency.

本文提出了一个理论公式，用于通过均质化方法对多孔复合夹层板进行屈曲分析。通过比较有限元分析和实验分析的结果，验证了理论公式的有效性。最后，理论公式用于优化具有多个孔的复合夹层板，用于设计飞机结构以最小化质量。优化结果允许获得用于航空航天应用的具有多个孔的复合夹层结构的屈曲特性的数据库。