复合材料混合连接结构拉伸性能与影响因素分析

黄文俊; 程小全; 武鹏飞; 李钟海

复合材料混合连接结构拉伸性能与影响因素分析

1.
南京航空航天大学航空宇航学院, 南京210016
2. 北京航空航天大学航空科学与工程学院, 北京 100191

详细信息

作者简介:
黄文俊(1972-),男,江西临川人,博士生,chrdihwj@163.com.

中图分类号: TB332
计量
- 文章访问数: 1705
- HTML全文浏览量: 217
- PDF下载量: 1314
- 被引次数: 0
出版历程
- 收稿日期: 2012-12-28
- 网络出版日期: 2013-10-30

Analysis on tensile properties and influence factors of composite hybrid joints

1.
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2. School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 胶螺混合连接设计适当,能够提高结构的连接效率.针对复合材料胶螺(螺钉)混合连接结构中存在的分析与设计问题,在ABAQUS软件平台上建立了损伤累积三维有限元模型,其中考虑了胶层物理非线性以及非线性接触等问题,连接结构拉伸强度及损伤破坏过程的计算结果与试验结果基本吻合,证明了所建模型的有效性.在此基础上,研究了复合材料层合板端头翻边、胶层厚度、胶层韧性以及接触面摩擦系数等因素的影响.结果表明:复合材料层合板端头翻边对混合连接结构具有增强作用,能够提高结构的拉伸强度;韧性胶层能够提高结构的拉伸强度,但胶层厚度对结构的强度基本没有影响;螺钉杆与连接孔接触面间摩擦系数越大,连接结构的拉伸强度越高.
- 复合材料层合板 /
- 胶螺混合连接 /
- 拉伸 /
- 强度 /
- 损伤
Abstract: Proper bolted or screw / bonded hybrid joint design can improve the structure efficiency. In order to solve the analysis and design problems that exist in screw / bonded hybrid composite joint structures, a 3D damage accumulation finite element analysis (FEA) model was established based on the software of ABAQUS. Non-linear properties of the adhesives and non-linear touch problems were included in this model. The analysis results of the tensile strength and damage propagation and failure of the joint structures agree with the test results. And the model effectiveness was proved. Then the influence factors such as the flange at the tip of the laminates, adhesive film thickness, adhesive toughness and contact surface friction coefficients on the joint tensile properties were studied. The results show that the flange at the laminate tip can reinforce the hybrid joint structures and improve their tensile strength. Adhesive with high toughness can improve the joint tensile strength and the film thickness almost has no effect on the strength. Higher friction coefficient between the screw pin and the hole surface can give greater joint tensile strength.
- composite laminate /
- screw / bonded hybrid joint /
- tension /
- strength /
- damage

HTML全文

参考文献(1)

[1] Kelly G.Load transfer in hybrid (bonded/bolted) composite single-lap joints [J].Composite Structures,2005,69(1):35-43 [2] Gomez S,Onoro J,Pecharroman J.A simple mechanical model of a structural hybrid adhesive/riveted single lap joint [J].International Journal of Adhesion & Adhesives,2007,27(4):263-267 [3] Barut A,Madenci E.Analysis of bolted-bonded composite single-lap joints under combined in-plane and transverse loading [J].Composite Structures,2009,88(4):579-594 [4] Sadowski T,Knec M,Golewski P.Experimental investigations and numerical modeling of steel adhesive joints reinforced by rivets [J].International Journal of Adhesion & Adhesives,2010,30(5):338-346 [5] Ding K,Dhanasekar M.Flexural behavior of bonded-bolted butt joints due to bolt looseness [J].Advances in Engineering Software,2007,38(8-9):598-606 [6] Ryosuke M,Motoko S,Akira T.Improving performance of GFRP/aluminum single lap joints using bolted/co-cured hybrid method [J].Composites:Part A,2008,39(2):154-163 [7] Fu M F,Mallick P K.Fatigue of hybrid (adhesive/bolted) joints in SRIM composites [J].International Journal of Adhesion & Adhesives,2001,21(2):145-159 [8] Hoang-Ngoc C T,Paroissien E.Simulation of single-lap bonded and hybrid (bolted/bonded) joints with flexible adhesive [J].International Journal of Adhesion & Adhesives,2010,30(3):117-129 [9] Kweon J H,Jung J W,Kim T H,et al.Failure of carbon composite-to-aluminum joints with combined mechanical fastening and adhesive bonding [J].Composite Structures,2006,75(1/2/3/4):192-198 [10] 程小全,汪源龙,张纪奎,等.平面编织复合材料胶螺混合连接接头拉伸性能分析[J].固体力学学报,2011,32(4):346-352 Cheng Xiaoquan,Wang Yuanlong,Zhang Jikui,et al.Tensile performance analysisi of combined adhesive and bolted joints for plain woven composites [J].Chinese Journal of Solid Mechanics,2011,32(4):346-352(in Chinese) [11] 陈浩然,息志臣.复合材料机械连接件非线性接触应力分析[J].航空学报,1990,11(7):410-414 Chen Haoran,Xi Zhichen. Nonlinear contact stress analysis of composite bolted joints [J].Acta Aeronautica et Astronautica Sinica,1990,11(7):410-414(in Chinese) [12] 陈浩然,息志臣.具有销钉承载孔的复合材料层合板的接触应力分析 [J].航空学报,1990,11(8):379-382 Chen Haoran,Xi Zhichen.Contact stress analysis of composite laminate with pin-loaded holes [J].Acta Aeronautica et Astronautica Sinica,1990,11(8):379-382(in Chinese) [13] Tserpes K I,Papanikos P,Labeas G,et al.Fatigue damage accumulation and residual strength assessment of CFRP laminates [J].Composite Structures,2004,63(2):219-230 [14] Papanikos P,Tserpes K I,Labeas G,et al.Progressive damage modeling of bonded composite repairs [J].Theoretical and Applied Fracture Mechanics,2005,43(2):189-198 [15] Yi X,Takashi I.Bearing strength and failure behavior of bolted composite joints (part II:modeling and simulation) [J].Composites Science and Technology,2005,65(7/8):1032-1043 [16] Kallmeyer A R,Stephens R I.Finite element model for predicting time-dependent deformations and damage accumulation in laminated composite bolted joints [J].Journal of Composite Materials,1999,33(9):794-826 [17] Reifsnider K,Case S.The mechanics of composite strength evolution [J].Composite Science and Technology,2000,60(12/13):2539-2546 [18] Kim Y M,Hong C S.Progressive failure model for the analysis of laminated composites based on finite element approach [J].Journal of Reinforced Plastics and Composites,1992,11(10):1078-1092 [19] Chang F K,Springer G S.Strengths of fiber reinforced composite bends [J].Journal of Composite Materials,1986,20(1):30-45 [20] Tserpes K I,Labeas G.Strength prediction of bolted joints in graphite/epoxy composite laminates [J].Composite Part B:Engineering,2002,33(7):521-529 [21] Tserpes K I,Papanikos P,Kermanidis T.A three-dimensional progressive damage model for bolted joints in composite laminates subjected to tensile loading [J].Fatigue and Fracture of Engineering Materials and Structures,2002,24(10):673-686 [22] Riccio A,Scaramuzzino F.Embedded delamination growth in composite panels under compressive load [J].Composites:Part B,2001,32(3):209-218

施引文献

资源附件(0)

访问统计