整体复合材料结构分层特性研究进展(一)  

Development on Delamiantion Characteristics of Integrated Composite Structures:Part I

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5期31-39,共9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研究综述的第一部分,重点介绍界面断裂力学和应力分析方法。论文首先对复合材料失效和分层研究进行了简要的回顾,然后详细介绍了界面断裂力学发展的历史、基本公式和在复合材料分层研究中的应用,并且介绍了几种界面裂纹尖端场的求解方法——J积分、修正的裂纹闭合积分(Modified Crack Closure Integral)和M积分法。其次,对应力分析在复合材料分层研究中的应用进行了简要的回顾。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 first part for the overview of delamiantion characteristics of integrated composite structures. First, the failure styles and delaminaiton research for composite materials were viewed in this paper, then, the development history, basic equations and recent applications were introduced, and the several computation ways for interface crack tip fields were expounded, which include in J integral, Modified crack closure integral and M integral. The stress methods in delamination analysis are introduced in the second section in this paper.

关 键 词：复合材料结构 分层特性 界面断裂力学 应力分析 

分 类 号：TB332[一般工业技术—材料科学与工程]