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CFRP平-折-平连接接头试验研究与数值模拟

许昶 刘志明

许昶, 刘志明. CFRP平-折-平连接接头试验研究与数值模拟[J]. 北京航空航天大学学报, 2019, 45(11): 2207-2216. doi: 10.13700/j.bh.1001-5965.2019.0062
引用本文: 许昶, 刘志明. CFRP平-折-平连接接头试验研究与数值模拟[J]. 北京航空航天大学学报, 2019, 45(11): 2207-2216. doi: 10.13700/j.bh.1001-5965.2019.0062
XU Chang, LIU Zhiming. Experimental study and numerical simulation on CFRP flat-joggle-flat joints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(11): 2207-2216. doi: 10.13700/j.bh.1001-5965.2019.0062(in Chinese)
Citation: XU Chang, LIU Zhiming. Experimental study and numerical simulation on CFRP flat-joggle-flat joints[J]. Journal of Beijing University of Aeronautics and Astronautics, 2019, 45(11): 2207-2216. doi: 10.13700/j.bh.1001-5965.2019.0062(in Chinese)

CFRP平-折-平连接接头试验研究与数值模拟

doi: 10.13700/j.bh.1001-5965.2019.0062
基金项目: 

国家重点研发计划 2016YFB1200505-011

详细信息
    作者简介:

    许昶  男, 博士研究生。主要研究方向:复合材料结构设计

    刘志明  男, 博士, 教授, 博士生导师。主要研究方向:结构疲劳及其可靠性

    通讯作者:

    刘志明.E-mail:zhmliu1@bjtu.edu.cn

  • 中图分类号: TB331

Experimental study and numerical simulation on CFRP flat-joggle-flat joints

Funds: 

National Key R & D Program of China 2016YFB1200505-011

More Information
  • 摘要:

    针对碳纤维增强复合材料(CFRP)平-折-平(FJF)连接接头强度和失效问题进行了试验研究和数值模拟。基于商用有限元软件ABAQUS,建立了FJF连接接头强度预测模型,通过与试验结果进行对比,探究了此类接头在拉伸载荷工况下的失效形式和承载能力,同时分析了搭接长度对接头强度和失效模式的影响。结果表明,利用模型预测的接头承载能力与试验结果的误差均小于3.5%,具有较好的精度。不同搭接长度下,FJF混合连接接头相较于胶接连接接头和机械连接接头强度均有提升。接头的强度随着搭接长度的增大而增大,搭接长度增大到一定程度后趋于平缓。搭接长度较小时,FJF混合连接接头失效表现为胶层沿搭接区的断裂和孔边挤压失效;搭接长度较大时,失效模式转变为层合板孔边拉伸断裂和胶层扩展至孔边的断裂。

     

  • 图 1  胶层材料拉伸应力-应变关系

    Figure 1.  Tensile stress-strain relationship of adhesive material

    图 2  FJF胶接连接接头示意图

    Figure 2.  Schematic diagram of FJF bonded joint

    图 3  FJF机械连接接头示意图

    Figure 3.  Schematic diagram of FJF bolted joint

    图 4  FJF混合连接接头示意图

    Figure 4.  Schematic diagram of FJF hybrid joint

    图 5  拉伸测试设备

    Figure 5.  Tensile testing equipment

    图 6  胶层失效分析VUMAT流程图

    Figure 6.  VUMAT flowchart for failure analysis of the adhesive layer

    图 7  带孔层合板渐进损伤分析VUMAT流程图

    Figure 7.  VUMAT flowchart for progressive damage analysis of the composite laminate with holes

    图 8  3种FJF连接接头拉伸载荷-位移曲线

    Figure 8.  Tensile load-displacement curves of three kinds of FJF joints

    图 9  3种FJF连接接头极限载荷对比

    Figure 9.  Ultimate load comparison of three kinds of FJF joints

    图 10  3种FJF连接接头载荷-位移曲线

    Figure 10.  Load-displacement curves of three kinds of FJF joints

    图 11  FJF胶接连接接头胶层即将失效时等效塑性应变

    Figure 11.  Equivalent plastic strain of FJF bonded joint when adhesive layer is about to fail

    图 12  FJF机械连接接头失效图

    Figure 12.  Failure of FJF bolted joint

    图 13  FJF混合连接接头失效图

    Figure 13.  Failure of FJF hybrid joint

    图 14  FJF混合连接接头载荷第一次下降时搭接区端部胶层开裂

    Figure 14.  Adhesive layer fracture at the end of overlap zone when load of FJF hybrid joint falls for the first time

    表  1  测试试样几何尺寸

    Table  1.   Geometry of testing specimen

    参数 数值
    孔径/mm 3.98
    未圆角长度/mm 45
    宽度/mm 16
    端距/mm 12
    层合板厚度/mm 2
    胶层厚度/mm 0.2
    较大圆角半径/mm 30
    较小圆角半径/mm 25.8
    平折段夹角/(°) 7.83
    下载: 导出CSV

    表  2  刚度退化准则

    Table  2.   Stiffness degradation rules

    失效模式 刚度退化准则
    纤维拉伸模式(σ1≥0) E1=0.07E1, E2=0.07E2, E3=0.07E3, ν12=0.14ν12, ν13=0.14ν13, ν23=0.14ν23
    纤维压缩模式(σ1 < 0) E1=0.14E1, E2=0.14E2, E3=0.14E3, ν12=0.14ν12, ν13=0.14ν13, ν23=0.14ν23
    基体拉伸模式(σ2≥0) E2=0.2E2, G12=0.2G12, G23=0.2G23
    基体压缩模式(σ2 < 0) E2=0.4E2, G12=0.4G12, G23=0.4G23
    纤-基剪切模式(σ1 < 0) G12=0, ν12=0
    拉伸分层模式(σ3≥0) E3=0, G13=0, G23=0,ν13=0, ν23=0
    压缩分层模式(σ3 < 0) E3=0, G13=0, G23=0,ν13=0, ν23=0
    下载: 导出CSV

    表  3  不同水平搭接段长度下FJF连接接头强度对比

    Table  3.   Strength comparison of FJF joints under different horizontal lap lengths

    水平搭接段长度/ mm 胶接连接接头强度/kN 机械连接接头强度/kN 混合连接接头强度/kN 混合连接接头相较于胶接连接接头/% 混合连接接头相较于机械连接接头/%
    25 9.24 9.38 11.93 +29.1 +27.2
    35 9.61 10.03 13.64 +41.9 +36.0
    45 9.84 10.40 13.77 +39.9 +32.4
    下载: 导出CSV
  • [1] 周伟旭.碳纤维增强树脂基复合材料在轨道交通车辆车体中的应用与思考[J].城市轨道交通研究, 2018(12):10-13. http://d.old.wanfangdata.com.cn/Periodical/csgdjtyj201812004

    ZHOU W X.On the application of carbon fiber reinforced polymer to rail transit composite carbody[J].Urban Mass Transit, 2018(12):10-13(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/csgdjtyj201812004
    [2] 彭大伟.中国中车在全球最大轨道交通展发布新一代碳纤维地铁[EB/OL].(2018-09-19)[2019-04-23].http://www.chinanews.com/cj/2018/09-19/8630913.shtml.

    PENG D W.CRRC launched a new generation of carbon fiber subway at the world largest rail transit exhibition[EB/OL].(2018-09-19)[2019-04-23].http://www.chinanews.com/cj/2018/09-19/8630913.shtml(in Chinese).
    [3] 赵丽滨, 徐吉峰.先进复合材料连接结构分析方法[M].北京:北京航空航天大学出版社, 2015:73-74.

    ZHAO L B, XU J F.Analytic method of joints for advanced composite materials[M].Beijing:Beihang University Press, 2015:73-74(in Chinese).
    [4] CHOWDHURY N M, WANG J, CHIU W K, et al.Static and fatigue testing bolted, bonded and hybrid step lap joints of thick carbon fibre/epoxy laminates used on aircraft structures[J].Composite Structures, 2016, 142:96-106. doi: 10.1016/j.compstruct.2016.01.078
    [5] FERNÁNDEZ-CANÑADAS L M, IVÁÑEZ I, SANCHEZ-SAEZ S.Influence of the cohesive law shape on the composite adhesively-bonded patch repair behaviour[J].Composites Part B:Engineering, 2016, 91:414-421. doi: 10.1016/j.compositesb.2016.01.056
    [6] HESHMATI M, HAGHANI R, AL-EMRANI M, et al.On the strength prediction of adhesively bonded FRP-steel joints using cohesive zone modelling[J].Theoretical and Applied Fracture Mechanics, 2018, 93:64-78. doi: 10.1016/j.tafmec.2017.06.022
    [7] MATTA S, RAMJI M.Prediction of mechanical behaviour of adhesively bonded CFRP scarf jointed specimen under tensile loading using localised DIC and CZM[J].International Journal of Adhesion and Adhesives, 2019, 89:88-108. doi: 10.1016/j.ijadhadh.2018.12.002
    [8] 徐云研, 程小全, 张纪奎, 等.复合材料蜂窝夹层结构T型接头拉伸性能研究[J].工程力学, 2015, 32(7):243-248. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=gclx201507032

    XU Y Y, CHENG X Q, ZHANG J K, et al.Study on composite honeycomb sandwich structure formed T-joints under tensile load[J].Engineering Mechanics, 2015, 32(7):243-248(in Chinese). http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=gclx201507032
    [9] SENTHIL K, AROCKIARAJAN A, PALANINATHAN R.Numerical study on the onset of initiation of debond growth in adhesively bonded composite joints[J].International Journal of Adhesion and Adhesives, 2018, 84:202-219. doi: 10.1016/j.ijadhadh.2018.03.009
    [10] JOSEPH A P K, DAVIDSON P, WAAS A M.Open hole and filled hole progressive damage and failure analysis of composite laminates with a countersunk hole[J].Composite Structures, 2018, 203:523-538. doi: 10.1016/j.compstruct.2018.06.120
    [11] YANG Y X, LIU X S, WANG Y Q, et al.A progressive damage model for predicting damage evolution of laminated composites subjected to three-point bending[J].Composites Science and Technology, 2017, 151:85-93. doi: 10.1016/j.compscitech.2017.08.009
    [12] ZHAO L B, YANG W, CAO T C, et al.A progressive failure analysis of all-C/SiC composite multi-bolt joints[J].Composite Structures, 2018, 202:1059-1068. doi: 10.1016/j.compstruct.2018.05.029
    [13] RICCIO A, DI COSTANZO C, DI GENNARO P, et al.Intra-laminar progressive failure analysis of composite laminates with a large notch damage[J].Engineering Failure Analysis, 2017, 73:97-112. doi: 10.1016/j.engfailanal.2016.12.012
    [14] MARANNANO G, ZUCCARELLO B.Numerical experimental analysis of hybrid double lap aluminum-CFRP joints[J].Composites Part B:Engineering, 2015, 71:28-39. doi: 10.1016/j.compositesb.2014.11.025
    [15] ARMENTANI E, LAISO M, CAPUTO F, et al.Numerical FEM evaluation for the structural behaviour of a hybrid (bonded/bolted) single-lap composite joint[J].Procedia Structural Integrity, 2018, 8:137-153. doi: 10.1016/j.prostr.2017.12.015
    [16] 孟毛毛, 赵美英, 弥晓亮, 等.胶-螺混合连接结构强度分析及影响因素研究[J].航空工程进展, 2013, 4(2):186-192. doi: 10.3969/j.issn.1674-8190.2013.02.009

    MENG M M, ZHAO M Y, MI X L, et al.Analysis of the bonded-bolted hybrid composite joints' strength and influences[J].Advances in Aeronautical Science and Engineering, 2013, 4(2):186-192(in Chinese). doi: 10.3969/j.issn.1674-8190.2013.02.009
    [17] KISHORE A N, PRASAD N S.An experimental study of flat-joggle-flat bonded joints in composite laminates[J].International Journal of Adhesion and Adhesives, 2012, 35(7):55-58. http://www.wanfangdata.com.cn/details/detail.do?_type=perio&id=e22a381c6024f6bee9c243f462d5da51
    [18] 王毅, 冯宪章, 李磊, 等.复合材料层合板二次共固化补强胶层失效分析研究[J].机械强度, 2012, 34(6):862-867.

    WANG Y, FENG X Z, LI L, et al.Bonding adhesive damage study of the secondary co-cure reinforcement tensile experiment[J].Journal of Mechanical Strength, 2012, 34(6):862-867(in Chinese).
    [19] MCARTHY M A, MCCARTHY C T, LAWLOR V P, et al.Three-dimensional finite element analysis of single-bolt, single-lap composite bolted joints:Part Ⅰ-model development and validation[J].Composite Structures, 2005, 71(2):140-158. doi: 10.1016/j.compstruct.2004.09.024
    [20] ASHITH P K J, PAUL D, ANTHONY M W.Progressive damage and failure analysis of single lap shear and double lap shear bolted joints[J].Composites Part A, 2018, 113:264-274. doi: 10.1016/j.compositesa.2018.07.018
    [21] HU X F, HARIS A, RIDHA M, et al.Progressive failure of bolted single-lap joints of woven fibre-reinforced composites[J].Composite Structures, 2018, 189:443-454. doi: 10.1016/j.compstruct.2018.01.104
    [22] 李占伟.复合材料层合板损伤失效模拟分析[D].哈尔滨: 哈尔滨工程大学, 2012: 20-21. http://cdmd.cnki.com.cn/Article/CDMD-10217-1012517948.htm

    LI Z W.Simulation analysis of composite laminate failure[D].Harbin: Harbin Engineering University, 2012: 20-21(in Chinese). http://cdmd.cnki.com.cn/Article/CDMD-10217-1012517948.htm
    [23] TSERPES K I, LABEAS G, PAPANIKOS P, et al.Strength prediction of bolted joints in graphite/epoxy composite laminate[J].Composite Part B:Engineering, 2002, 33:521-529. doi: 10.1016/S1359-8368(02)00033-1
    [24] 李进亚.复合材料蜂窝夹芯板低速冲击损伤研究[D].南京: 南京航空航天大学, 2012: 10-11. http://www.cnki.com.cn/Article/CJFDTotal-FUHE803.023.htm

    LI J Y.Studies on low-velocity impact damage of composite honeycomb sandwich panel[D].Nanjing: Nanjing University of Aeronautics and Astronautics, 2012: 10-11(in Chinese). http://www.cnki.com.cn/Article/CJFDTotal-FUHE803.023.htm
    [25] FIONN D, NIK P.Introduction to computational plasticity[M].Oxford:Oxford University Press, 2005:175-176.
    [26] 王佩艳, 王富生, 朱振涛, 等.复合材料机械连接件的三维累积损伤研究[J].机械强度, 2010, 32(5):814-818. http://d.old.wanfangdata.com.cn/Periodical/jxqd201005024

    WANG P Y, WANG F S, ZHU Z T, et al.3D numerical calculation of damage accumulation for composite single bolted joint[J].Journal of Mechanical Strength, 2010, 32(5):814-818(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/jxqd201005024
    [27] 姜晓伟, 曾建江, 曾昭炜, 等.配合方式对复合材料单钉单剪螺栓连接接头刚度的影响及其机制[J].复合材料学报, 2016, 33(3):589-596. http://d.old.wanfangdata.com.cn/Periodical/fhclxb201603019

    JIANG X W, ZENG J J, ZENG S W, et al.Influence and mechanism of fitting mode on stiffness of single-bolt, single-lap composite bolted joint[J].Acta Materiae Compositae Sinica, 2016, 33(3):589-596(in Chinese). http://d.old.wanfangdata.com.cn/Periodical/fhclxb201603019
    [28] 梁祖典, 燕瑛, 张涛涛, 等.复合材料单搭接胶接接头试验研究与数值模拟[J].北京航空航天大学学报, 2014, 40(12):1786-1792. https://bhxb.buaa.edu.cn/CN/abstract/abstract13114.shtml

    LIANG Z D, YAN Y, ZHANG T T, et al.Experimental investigation and numerical simulation of composite laminate adhesively bonded single-lap joints[J].Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(12):1786-1792(in Chinese). https://bhxb.buaa.edu.cn/CN/abstract/abstract13114.shtml
    [29] 孙中雷, 张国凡.复合材料胶接接头强度设计研究[J].计算机仿真, 2017, 34(3):46-50. doi: 10.3969/j.issn.1006-9348.2017.03.011

    SUN Z L, ZHANG G F.Strength design of adhesively bonded composite double-lap joints[J].Computer Simulation, 2017, 34(3):46-50(in Chinese). doi: 10.3969/j.issn.1006-9348.2017.03.011
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  • 收稿日期:  2019-02-22
  • 录用日期:  2019-04-19
  • 刊出日期:  2019-11-20

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