In this study, an analytical solution is presented to determine the buckling load of composite cylindrical shells with an auxetic honeycomb layer under a uniform axial load. The composite shell consists of three layers in which the core layer is made of the auxetic honeycomb structure with a negative Poisson’s ratio and the internal and external layers have been made of elastic and isotropic materials. The first-order shear deformation theory has been used as the displacement field. The equilibrium equations are determined by considering the von Kármán theory, and they are coupled nonlinear differential equations that are solved by employing the perturbation technique. The buckling load has been determined analytically by solving the stability equations, which are a system of coupled differential equations with variable coefficients. By conducting a parametric study, the effects of the honeycomb structure and the aspect ratios on the buckling load have been investigated. It is seen that by changing the geometrical parameters of the honeycomb structure, the Poisson ratio can be adjusted and the mechanical behavior of the composite shell has been modified. The results are compared with some other references and the finite element analysis.

在这项研究中，提出了一种解析解来确定在均匀轴向载荷下具有拉胀蜂窝层的复合圆柱壳的屈曲载荷。复合壳体由三层组成，芯层采用负泊松比拉胀蜂窝结构，内外层采用弹性各向同性材料。一阶剪切变形理论已被用作位移场。平衡方程是根据von Kármán理论确定的，它们是采用微扰技术求解的耦合非线性微分方程。屈曲载荷已通过求解稳定性方程来解析确定，稳定性方程是具有可变系数的耦合微分方程组。通过进行参数研究，研究了蜂窝结构和纵横比对屈曲载荷的影响。可以看出，通过改变蜂窝结构的几何参数，可以调整泊松比，并改变复合壳的力学行为。结果与一些其他参考文献和有限元分析进行了比较。