首页 | 本学科首页   官方微博 | 高级检索  
     检索      

缝合复合材料层合板拉伸疲劳损伤及其机理
引用本文:程小全,杨琨,胡仁伟,邹健.缝合复合材料层合板拉伸疲劳损伤及其机理[J].力学学报,2010,42(1).
作者姓名:程小全  杨琨  胡仁伟  邹健
作者单位:北京航空航天大学航空科学与工程学院,北京,100191
基金项目:国家自然科学基金(10672009);;航空基础科学基金(05B51044);;北京航空航天大学凡舟基金(20060501)资助项目~~
摘    要:对有、无缝合复合材料层合板的拉伸疲劳性能进行了试验研究,考察了0°缝合对复合材料光滑板拉伸疲劳损伤扩展规律的影响.通过有限元素法分析了有、无缝合复合材料层合板的应力状态分布情况,对缝合复合材料层合板的拉伸疲劳损伤及其扩展机理进行了分析.研究表明,缝合改变了复合材料层合板拉伸疲劳损伤起始与扩展的机理,针脚附近的面内正应力σ_x与层间剪应力的集中对层合板拉伸疲劳损伤的发生与扩展有着重要的作用,自由边界处的层间集中应力对缝合板的疲劳性能也有影响.自由边界处的层间集中应力是导致无缝合层合板疲劳损伤及其扩展的主要原因.

关 键 词:复合材料层合板  缝合  拉伸疲劳  损伤  机理

TENSILE FATIGUE DAMAGE AND ITS MECHANISM OF STITCHED COMPOSITE LAMINATES
Cheng Xiaoquan , Yang Kun , Hu Renwei , Zou Jian.TENSILE FATIGUE DAMAGE AND ITS MECHANISM OF STITCHED COMPOSITE LAMINATES[J].chinese journal of theoretical and applied mechanics,2010,42(1).
Authors:Cheng Xiaoquan  Yang Kun  Hu Renwei  Zou Jian
Institution:2;School of Aeronautical Science and Engineering/a>;Beijing University of Aeronautics and Astronautics/a>;Beijing 100191/a>;China
Abstract:Stitched laminate is a new kind of composite structure to improve the interface strength of composite. But the in-plane properties of the laminate may reduce because there are local fiber bending in the laminate plane and in the thickness direction,and the damage induced by the stitching threads.A lot of researches have been carried out on the properties of laminates to push this material into engineering applications,such as in-plane tension and compression,compression after impact,hygrothermal properties,...
Keywords:composite laminates  stitching  tensile fatigue  damage  mechanism  
本文献已被 CNKI 万方数据 等数据库收录!
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号