通过对含冲击损伤缝合复合材料层板进行压缩实验,揭示了含损伤缝合层板在压缩载荷下的破坏模式和破坏机制。将冲击损伤等效为圆孔,利用杂交单元计算冲击后缝合层板的应力分布,采用基于特征曲线概念的点应力判据预测了含损伤缝合层板的剩余压缩强度。研究结果表明:冲击损伤近似为圆形;缝合和未缝合层板冲击后压缩的损伤模式不同;采用开口等效法可以有效分析缝合层板的剩余压缩强度;特征距离、损伤面积是影响计算结果的主要因素。 By compressing the composite laminate with impact damage, the failure mode and failure mechanism of the damaged suture laminate under compressive load were revealed. The impact damage is equivalent to a circular hole. The stress distribution of the stitched laminates after impact is calculated by the hybridization unit. The residual compressive strength of the damaged stitched laminates is predicted by the point stress criterion based on the concept of characteristic curve. The results show that the impact damage is approximately circular, the different compression modes of sutured and non-sutured laminates are different, the residual compressive strength of suture laminates can be effectively analyzed by the open equivalent method, and the characteristic distance and lesion area affect the calculated results major factor.