复合材料层合板机械连接修理拉伸性能

聂恒昌; 谭日明; 郭霞; 关志东

doi:10.13700/j.bh.1001-5965.2015.0116

复合材料层合板机械连接修理拉伸性能

doi: 10.13700/j.bh.1001-5965.2015.0116

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

作者简介:
聂恒昌男,博士研究生。主要研究方向:飞机复合材料结构修理。Tel.:010-82338873 E-mail:nhc1991@126.com;关志东男,博士,教授,博士生导师。主要研究方向:飞机复合材料结构设计。Tel.:010-82338873 E-mail:zdguan@buaa.edu.cn

通讯作者:
关志东,Tel.:010-82338873 E-mail:zdguan@buaa.edu.cn

中图分类号: V214.8
计量
- 文章访问数: 962
- HTML全文浏览量: 153
- PDF下载量: 588
- 被引次数: 0
出版历程
- 收稿日期: 2015-03-06
- 网络出版日期: 2016-02-20

Tensile performances of mechanically fastened repairs of composite laminates

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

摘要: 带损伤孔的复合材料层合板拉伸强度会降低约55%,需要对其进行修理以恢复力学性能、满足使用要求。针对带圆形损伤孔的复合材料层合板设计了机械连接修理方案,通过轴向拉伸试验评估其修理效果。根据试验条件建立了有限元模型,分析不同的修理方案对破坏模式、破坏载荷、应力分布、钉载分配等产生的影响。试验及有限元分析(FEA)均表明,修理后的复合材料层合板,其强度恢复率达到55%~60%左右,应力集中部位主要在修理区域最外侧的钉孔旁,最终破坏模式为母板沿修理区域最外侧一排钉孔断裂。使用双面修理、增加螺栓排数、采用金属补片、适当增加补片厚度,可减缓应力集中,改善钉载分配,提高结构强度恢复率。
- 层合板 /
- 机械连接修理 /
- 有限元分析(FEA) /
- 破坏模式 /
- 强度恢复率 /
- 渐进损伤 /
- 钉载分配
Abstract: Composite laminates with a damage hole, whose strength will reduce by about 55% under tensile loads, need to be repaired in order to recover their mechanical properties and meet the usage requirements. Mechanically fastened repair projects of composite laminates with a circular hole were designed and the repair effects were evaluated by tensile tests. Finite element models were established according to test condition, from which the effects of different repair projects on the failure loads, failure modes, stress distributions, and bolt load distributions were analyzed. The results of tests and finite element analysis (FEA) show that the recovery rate of failure strength of bolted repaired laminates will reach about 55%-60%. The areas beside the outermost bolt holes in the repair area of the laminates mainly produce stress concentration. The final failure mode of the laminates is breaking along the outermost bolt holes in the repair area. Methods such as double patch repair, adding fastened bolts, using a metal patch and increasing the thickness of patch properly can reduce stress concentration, improve bolt load distributions and enhance the recovery rate of structural failure strength.
- laminates /
- mechanically fastened repair /
- finite element analysis (FEA) /
- failure mode /
- recovery rate of failure strength /
- progressive damage /
- bolt load distribution

HTML全文

参考文献(23)

[1]	杜善义,关志东.我国大型客机先进复合材料应对策略思考[J].复合材料学报, 2008,25(1):1-10. DU S Y,GUAN Z D.Strategic considerations for development of advanced composite technology for large commercial aircraft in China[J].Acta Materiae Compositae Sinica,2008,25(1):1-10(in Chinese).
[2]	KATNAM K B,DA SILVA L F M,YOUNG T M.Bonded repair of composite aircraft structures:A review of scientific challenges and opportunities[J].Progress in Aerospace Sciences,2013,61:26-42.
[3]	ARMSTRONG K B,GRAHAM BEVAN L,COLE II W F.Care and repair of advanced composites[M].2nd ed.Warrendale:SAE International,2005:258-266.
[4]	FLYNN B W,BODINE J B,DOPKER B,et al.Advance technology composite fuselage-Repair and damage assessment supporting maintenance:NASA-CR-4733[R].Washington,D.C.:NASA,1997:A1-A8.
[5]	陈绍杰.复合材料结构修理指南[M].北京:航空工业出版社,2001:66-74. CHEN S J.Manual of repaired of composite structures[M].Beijing:Aviation Industry Press,2001:66-74(in Chinese).
[6]	DUONG C N,WANG C H.Composite repair-theory and design[M].Amsterdam:Elsevier,2007:4-5.
[7]	DANO M L,KAMAL E,GENDRON G.Analysis of bolted joints in composite laminates:Strains and bearing stiffness predictions[J].Composite Structures,2007,79(4):562-570.
[8]	ZHANG J Y,LIU F R,ZHAO L B,et al.A progressive damage analysis based characteristic length method for multi-bolt composite joints[J].Composite Structures,2014,108(1):915-923.
[9]	YUN J H,CHOI J H,KWEON J H.A study on the strength improvement of the multi-bolted joint[J].Composite Structures,2014,108(1):409-416.
[10]	ZHANG J M.Design and analysis of mechanically fastened composite joints and repairs[J].Engineering Analysis with Boundary Elements,2001,25(6):431-441.
[11]	BOHLMANN R E,RENIERI G D,RILEY B L.Bolted composite repairs subjected to biaxial or shear loads[C]//Composite Materials:Testing and Design (Seventh Conference).West Conshohocken,PA:WHITNEY J M,1986:34-47.
[12]	BOHLMANN R E,RENIERI G D,RILEY B L.Bolted field repair of graphite/epoxy wing skin laminates[J].ASTM Special Technical Publication,1981,749:97-116.
[13]	HER S C,SHIE D L.The failure analysis of bolted repair on composite laminate[J].International Journal of Solids and Structures,1998,35(15):1679-1693.
[14]	KRADINOV V,HANAUSKA J,BARUT A,et al.Bolted patch repair of composite panels with a cutout[J].Composite Structures,2002,56(4):423-444.
[15]	WANG C H,GUNNION A J,ORIFICI A C,et al.Effect of load-bypass on structural efficiencies of bonded and bolted repairs[C]//The 17th International Conference on Composite Materials.Edinburgh:ICCM,2009:20113514273406.
[16]	李旭东,关志东.整体壁板损伤容限特性与修理技术研究[J].中国民航大学学报,2008,26(5):36-38. LI X D,GUAN Z D.Investigation of fuselage integral panel repair technology[J].Journal of Civil Aviation University of China,2008,26(5):36-38(in Chinese).
[17]	赵美英,万小朋,刘浩.复合材料螺接修补参数优化[J].航空学报,2008,22(5):458-460. ZHAO M Y,WAN X P,LIU H.Optimization of composite patch bolted repairing parameters[J].Acta Aeronautica et Astronautica Sinica,2008,22(5):458-460(in Chinese).
[18]	杜奎,黎增山,何为,等.机械连接修理对圆孔应力集中系数影响研究[C]//第十四届中国科协年会第11分会场:低成本、高性能复合材料发展论坛论文集.北京:中国科学技术协会,2012:22-27. DU K,LI Z S,HE W,et al.The influence of mechanical connection repair for circle hole stress concentration coefficient[C]//Proceedings of the 14th Annual Meeting of China Association for Science and Technology.Beijing:China Association for Science and Technology, 2012:22-27(in Chinese).
[19]	赵闯,黎增山,康军,等.复合材料加筋板大开口结构拉伸与修理性能[J].航空制造技术,2013(23-24):125-130. ZHAO C,LI Z S,KANG J,et al.Tensile performance and repair performance of composites stiffened panel with large cutout[J].Aeronautical Manufacturing Technology,2013(23-24):125-130(in Chinese).
[20]	赵闯,聂恒昌,郭霞,等.复合材料加筋板筋条修理后的压缩性能[J].北京航空航天大学学报,2014,40(6):834-838. ZHAO C,NIE H C,GUO X,et al.Compression performance of composite stiffened panel after stiffener repair[J].Journal of Beijing University of Aeronautics and Astronautics,2014,40(6):834-838(in Chinese).
[21]	蓝元沛,徐吉峰,杜奎.剪切载荷作用下复合材料挖补修理层合板试验及有限元分析[J].复合材料学报,2014,31(3):803-808. LAN Y P,XU J F,DU K.Experimental study and FEA on composite flush-repair laminates under shear load[J].Acta Materiae Compositae Sinica,2014,31(3):803-808(in Chinese).
[22]	HASHIN Z.Failure criteria for unidirectional fiber composites[J].Journal of Applied Mechanics,1980,47(2):329-334.
[23]	谢鸣九.复合材料多排机械连接钉载分配研究[C]//第十五届全国复合材料学术会议论文集(下册).哈尔滨:中国复合材料学会,2008:1165-1167. XIE M J.Analysis research on load distribution for multirow fastened joint in fibrous composites[C]//Proceedings of National Conference on Composite Materials-15(II).Harbin:Chinese Society for Composite Materials,2008:1165-1167(in Chinese).