复合材料层合板分层损伤数值模拟方法研究现状  

Status of numerical simulation methods for delamination damage of composite laminates

作　　者：李西宁[1] 王悦舜 周新房 LI Xining;WANG Yueshun;ZHOU Xinfang(School of Mechanical Engineering,Northwestern Polytechnical University,Xi'an 710072,China;Department of Manufacturing Engineering,AVIC Xi’an Aircraft Industry CO.LTD.,Xi’an710089,China)

机构地区：[1]西北工业大学机电学院,西安710072 [2]中航工业西安飞机工业有限责任公司制造工程部,西安710089

出　　处：《复合材料学报》2021年第4期1076-1086,共11页Acta Materiae Compositae Sinica

摘　　要：复合材料层合板在航空航天等领域受到广泛应用,分层损伤作为复合材料层合板主要的损伤形式,对复合材料结构的强度和刚度有显著的影响,是限制其重大工程应用的热点问题之一。通过实验的方法对复合材料结构进行研究,往往需要耗费大量的时间和成本,成熟的有限元数值模拟技术可以较低成本实现复合材料结构的分层行为模拟,成为分层损伤研究的重要手段。本文从数值模拟角度总结了国内外在纤维增强复合材料分层损伤取得的研究成果,并对目前主要的方法虚拟裂纹闭合技术(VCCT)、内聚力模型(CZM)及扩展有限元法(XFEM)进行阐述。最后,对其发展方向进行了展望。Composite laminates are widely used in aerospace and other fields.Delamination is the main damage form in composite laminates,which has a significant impact on the strength and stiffness of composite structures.It’s one of the hot issues which is limited in major engineering applications.It often takes a lot of time and cost to study composite structure by experimental methods.Mature finite element numerical simulation technology can realize the layered behavior simulation of composite structures at a low cost and become an important means for delamination damage research.In this paper,from the perspective of numerical simulation,the research results on the interface damage of fiber reinforced composite materials at home and abroad are summarized,and the current main methods are virtual crack closure technology(VCCT),cohesive force model(CZM)and extended finite element method(XFEM).Finally,the text makes a prospect for the future work.

关 键 词：分层损伤 数值模拟 虚拟裂纹闭合技术 内聚力模型 扩展有限元 

分 类 号：TB332[一般工业技术—材料科学与工程] V250[航空宇航科学与技术—航空宇航制造工程]