纤维增强树脂基复合材料因为其优异的性能在先进飞机结构中有着重要的前景，然而其在冲击载荷作用下的失效机理和失效模型还未完全澄清，成为制约其在航空航天领域应用的一个瓶颈，同时也引起国内外学者的广泛关注。本项目拟针对碳纤维增强环氧树脂基复合材料开展研究，通过设计层间I/II型裂纹动态断裂试验，结合高速摄像和显微分析技术，研究复合材料层合板在冲击载荷下的层间失效机理，发展基于动态J积分的断裂韧性评估方法，建立考虑应变率效应和纤维桥连机制的复合材料层间断裂失效模型，形成一套可用于数值计算的模型程序，并将其集成到已有仿真软件中。本项目的研究不仅对全面认识复合材料层间断裂行为的应变率效应有重要的科学意义,而且对于复合材料结构安全性设计具有重要的工程应用价值。

Fiber-reinforced resin-matrix composites have been considered as the most potential structural materials in the use of advanced airplanes. However, up to now, the failure mechanism of this kind of materials under impact loads remains unclear and an effective failure model is eagerly needed. This limits the development of composites in the field of aeronautics and aerospace, and has attracted much interest of researchers. This project will foucus on carbon fiber-reinforced epoxy-matrix composites.Firstly,the I/II modes dynamic fracture experiments will be designed and the delamination fracture mechanism of this composites under impact load will be carefully examined by means of high speed photography and microscopic observation.Method of dynamic fracture toughness evaluation will be developed based on the dynamic J-integral; Secondly, a delamination model will be established taking into account the strain rate effect as well as the fiber-bridging effect. A program based on this delamination moded will be developed and embedded into the comericial simulation software for easier application. This study is of great importance for understanding the strain rate effect on the delamination failure of composite materials and also for the safety design of composite structures in industrial applications.