整体复合材料结构分层特性研究进展(二)  

Development on Delamiantion Characteristics of Integrated Composite Structures:Part II

作　　者：马存旺[1] 李志国[1] 鲁国富 吴伟伟[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074 [2]中航工业特种飞行器研究所,湖北荆门448035

出　　处：《飞机设计》2014年第6期32-41,共10页Aircraft Design

摘　　要：整体复合材料件越来越多地被用作现代航空航天器的主承力结构,而分层是其最易出现的破坏形式。本文作为整体复合材料结构分层特性综述的第二部分,重点介绍了虚拟裂纹闭合技术和内聚区模型。论文首先对虚拟裂纹闭合技术的发展历史、基本公式和进行数值计算时需要注意的问题进行了阐述,介绍了该方法在复合材料分层研究中的最近应用情况。其次,详述了内聚区模型的发展历史、本构关系、界面参数,并对最近的应用情况进行了介绍。The integrated composite structures are is suitable for the principle bearing structures of aircraft, and delamination is the most common failure mode. This paper is the second part for the overview of delamiantion characteristics of integrated composite structures. The contents in this paper were focused on Virtual Crack Closure Technique（VCCT） and Cohesive zone model（CZM）. First, the development history, basic equations and some self-problems for VCCT were detailed expounded, then, the recent applications of VCCT in composite materials research were introduced. Second, the author summarized the history, constitutive equation and interface parameters, and the recent applications were introduced in this papper.

关 键 词：复合材料结构 研究方法 破坏准则 分层疲劳 

分 类 号：TB332[一般工业技术—材料科学与工程]