固化条件对分层损伤的层合板修理后强度的影响

详细信息    查看全文 | 推荐本文 |

英文篇名：Influence of curing condition on the residual strength of laminate repaired by delamination damage 作者：丁明惠 ; 詹帅 ; 王耕 ; 武郜宇 ; 金国 ; 马德权 英文作者：Ding Minghui;Zhan Shuai;Wang Geng;Wu Gaoyu;Jin Guo;Ma Dequan;Avic Harbin Aircraft Industry Group Co.,Ltd.;School of Astronautics,Harbin Institute of Technology;College of Materials Science and Chemical Engineering,Harbin Engineering University; 关键词：层合板 ; 挖补修理 ; 有限元模型 ; 剩余强度 英文关键词：laminate;;scarf repair;;finite element model;;residual strength 中文刊名：HGXC 英文刊名：New Chemical Materials 机构：中航工业哈尔滨飞机工业集团有限责任公司;哈尔滨工业大学航天学院;哈尔滨工程大学材料科学与化学工程学院; 出版日期：2018-01-15 出版单位：化工新型材料 年：2018 期：v.46;No.544 基金：国家自然科学基金(51371063,51575118) 语种：中文; 页：HGXC201801039 页数：5 CN：01 ISSN：11-2357/TQ 分类号：159-163

摘要

对(45/0/0/45)、(45/0/45/0/45)和(45/0/45/0/45/0/45)3种典型铺层形式复合材料层合板内部分层损伤分别在中温和常温固化条件下进行挖补修理。并且利用Patran/Nastran有限元计算软件对修理后的层合板进行模拟计算。研究结果表明:中温修理好于常温修理,只有4层铺层常温挖补修理不满足要求,而5层和7层修理后压缩强度和剪切强度均达到80%以上。5层铺层结构在常温挖补修理,压缩强度平均值达到175.83MPa,是原压缩强度的88.70%;剪切强度达到163.90MPa,是原剪切强度的82.90%。
        Three typical types of laminate(45/0/0/45),(45/0/45/0/45)and(45/0/45/0/45/0/45)with delamination damages were repaired by the scarf repair under middle temperature and room temperature.The simulation of repaired laminates were done by Patran/Nastran software.The results showed that the repairing efficiency was better by using middle temperature than room temperature.It was found that compressive strength recovered less than 80% strength of undamaged strength of samples for 4 layers structures by using room temperature repair.However,the strength could recover more than 80% strength of undamaged strength of samples for 5 and 7 layers structures.The average compressive strength of samples for 5 layers structures recovered to 175.83 MPa,88.70% of the undamaged strength of the samples by using room temperature repair,the average shear strength of samples recovered to 163.90 MPa,82.90% of undamaged strength of samples.

引文

[1]陈绍杰.复合材料结构修理指南[M].北京:航空工业出版社,2001,10-15.
    [2]薛克兴.复合材料结构的损伤与修补[M].北京:航空工业出版社,1992,20-25.
    [3]Jones J S,Graves S R.Repair techniques for Celion/LARC-160graphite/polyimide composite structures[J].NASA CR,1984,3794:6-7.
    [4]Found M S,Friend M J.Evaluation of CFRP panels with scarf repair patches[J].Composite Structures,1995,32(1):115-122.
    [5]孟凡颢,陈绍杰,童小燕.层压板修理设计中的参数选择问题[J].复合材料学报,2001,18(4):123-127.
    [6]Barut A,Hanauka J,Madenci E.Analysis method for bonded patch repair of a skin with a cutout[J].Composite Structures,2002,55:277-294.
    [7]Engels H,Becker W.Closed-form analysis for external patch repairs of laminates[J].Composite Structures,2002,56:259-268.
    [8]崔元庆.复合材料损伤结构胶接补强修补分析及设计技术[D].西安:西北工业大学力学与土木建筑学院,1999.
    [9]Soutis C,Hu F Z.Failure analysis of scarf-patch-repaired carbon fiber/epoxy laminates under compression[J].AIAA Journal,1998,38(4):737-740.
    [10]孟凡颢,陈绍杰,董善艳,等.复合材料损伤结构胶接补强修补分析及设计[J].飞机设计,2002(1):18-22.