以碳纤维增强环氧树脂基复合材料结构为研究对象,设计了含有预埋分层缺陷复合材料层合板的典型试件及压缩实验装置,采用试验与数值模拟相结合的方法,研究了分层缺陷位置、大小对结构压缩强度的影响。研究结果表明,分层缺陷的位置会改变层合板的分层形式,且小尺寸分层缺陷对于层合板的压缩强度几乎无影响。此结论可为复合材料结构应用于飞机结构的设计和制造提供依据。 Taking the carbon fiber reinforced epoxy resin matrix composite as the research object, a typical test piece and a compression experiment device containing a composite laminate with embedded delamination defects were designed. By combining the experimental and numerical simulation methods, the delamination defects Location, size of the structure of the compressive strength. The results show that the location of the delamination defects can change the layered form of the laminate, and the small size delamination defects have little effect on the compressive strength of the laminate. This conclusion may provide the basis for the application of composite structures to the design and manufacture of aircraft structures.