针对0o、45o、90o铺层角复合材料层合板的含孔结构损伤问题,提出了一种基于层合板各铺层孔边应力解析解的首次损伤载荷系数分析计算模型。根据非均匀各向异性层合板的弹性特性,采用复变函数曲线映射方法获取了层合板孔边界积分方程,计算获得了0o、45o、90o角度铺层层合板各铺层的孔边纤维主方向和垂直于纤维主方向的应力分量;采用Tsai-Hill强度理论,对层合板各铺层进行孔边首次损伤载荷系数计算。分析结果表明:试件左右两端面在受到均布拉伸载荷p的作用下,各铺层中具有90o铺层角的铺层首次损伤载荷系数最小,具有0o铺层角的铺层首次损伤载荷系数最大,说明具有90o铺层角的铺层最先出现损伤,对应铺层首次损伤出现在孔边90o方向区域。将计算值与现有文献结果进行比较,误差小于10%,二者具有较好的一致性。 Aiming at the problem of pore structure damage of 0o, 45o, 90o ply composite laminates, a first-time damage load factor analysis and calculation model based on the stress analysis of holes in laminate layers was proposed. According to the elastic properties of non-uniform anisotropic laminated plates, the integral equation of the boundary of laminated plate holes was obtained by using the complex function curve mapping method. The principal directions of the fiber at the edge of the laminated layers of 0 °, 45 °, 90 ° And the stress component perpendicular to the main direction of the fiber. The Tsai-Hill strength theory was used to calculate the first damage load coefficient of the holes on the laminate. The analysis results show that under the action of uniform tensile load p, the first damage load coefficient of the ply with 90o ply angle in each ply is the smallest, and the first damage load of the ply with 0o ply angle The coefficient is the largest, which indicates that the layer with the 90 ° bedding angle is the first to be damaged, and the first damage of the corresponding layer appears in the 90 ° direction of the hole. Comparing the calculated value with the existing literature results, the error is less than 10%, the two have good consistency.