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Volume 42 Issue 2
Feb.  2016
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Journal of Beijing University of Aeronautics and Astronautics  > 2016  >  42(2): 318-327.
NIE Hengchang, TAN Riming, GUO Xia, et al. Tensile performances of mechanically fastened repairs of composite laminates[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(2): 318-327. doi: 10.13700/j.bh.1001-5965.2015.0116(in Chinese)
Citation: NIE Hengchang, TAN Riming, GUO Xia, et al. Tensile performances of mechanically fastened repairs of composite laminates[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(2): 318-327. doi: 10.13700/j.bh.1001-5965.2015.0116(in Chinese)
shu

Tensile performances of mechanically fastened repairs of composite laminates

doi: 10.13700/j.bh.1001-5965.2015.0116

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

  • Received Date: 06 Mar 2015
  • Publish Date: 20 Feb 2016
    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.

     

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    • References(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).
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