Study on tensile properties of composite glue-screw hybrid connection structure with preload

doi:10.19936/j.cnki.2096-8000.20230728.010

Abstract

Abstract: On the basis of experimental verification of the feasibility of the simulation model, this paper analyzes the influence of pre-tightening force on the bearing capacity of CFRP/titanium alloy bolted connection and hybrid (bonded/bolted) connection structure under the mode of single nail and single lap. The results show that for CFRP/ titanium alloy bolted connection structure, the application of pre-tightening force can effectively increase the failure load of the joint, and the failure load of the joint with 2 N·m tightening torque and 3.5 N·m tightening torque is increased by 11.4% and 13.19% respectively, compared to that with 0.5 N·m tightening torque. For CFRP/ titanium alloy hybrid (bonded/bolted) connection structure, the increase of the failure load by pre-tightening force is weaker than that by bolt connection, but the simulation results of the scalar stiffness degradation (SDEG) of the adhesive layer show that the pre-tightening force can effectively reduce the diffusion of the peeling stress of the adhesive layer and slow down the failure of the adhesive layer.

Key words: hybrid (bonded/bolted) joint, bolt preload, single lap joint, adhesive layer failure, composites

CLC Number:

TB332

LI Haiyin, ZHENG Guoyan, WANG Lele, QI Jiaqi, ZHENG Yanping. Study on tensile properties of composite glue-screw hybrid connection structure with preload[J]. COMPOSITES SCIENCE AND ENGINEERING, 2023, 0(7): 72-78.

References

[1] 俸翔, 廖强, 何安荣, 等. 复合材料螺栓连接失效的数值模拟. 宇航材料工艺, 2013, 43(4): 87-90.
[2] ESENDEMIR M, AYE N. Effect of preload moment on the strength of mechanically fastened joints in woven glass-epoxy preprege. Materials Testing, 2018, 60(4): 423-430.
[3] BARUT A, MADENCI E. Analysis of bolted-bonded composite single-lap joints under combined in-plane and transverse loading. Composite Structures, 2009, 88(4): 579-594.
[4] ZHOU Y H, HAMED Y N, CHI H, et al. A three dimensional implicit finite element damage model and its application to single-lap multi-bolt composite joints with variable clearance. Composite Structures, 2015, 131: 1060-1072.
[5] 张超禹, 郑艳萍, 熊勇坚, 等. CFRP与铝板胶螺混合连接结构拉伸性能研究. 复合材料科学与工程, 2020(8): 12-17.
[6] 熊勇坚, 郑艳萍, 夏小松, 等. 金属-复合材料搭接结构性能研究. 玻璃钢/复合材料, 2019(8): 59-65.
[7] LI J, YAN Y, ZHANG T, et al. Experimental study of adhesively bonded CFRP joints subjected to tensile loads. International Journal of Adhesion and Adhesives, 2015, 57: 95-104.
[8] ESMAEILI F, CHAKHERLOU T N, ZEHSAZ M. Investigation of bolt clamping force on the fatigue life of double lap simple bolted and hybrid (bolted/bonded) joints via experimental and numerical analysis. Engineering Failure Analysis, 2014, 45: 406-420.
[9] 段元欣. CFRP螺栓干涉连接结构预紧行为及静强度研究. 西安: 西北工业大学, 2015.
[10] IOANNIS K G, DAMIAN D D, KYRIAKOS I K, et al. Effects of bolt torque tightening on the strength and fatigue life of airframe FRP laminate bolted joints. Composites Part B: Engineering, 2017, 125: 19-26.
[11] OLMEDO A, SANTIUSTE C. On the prediction of bolted single-lap composite joints. Composite Structures, 2012, 94(6): 2110-2117.
[12] SEN F, PAKDIL M, SAYMAN O, et al. Experimental failure analysis of mechanically fastened joints with clearance in composite laminates under preload. Materials & Design, 2008, 29(6): 1159-1169.
[13] TSERPES K I, LABEAS G, PAPANIKOS P, et al. Strength prediction of bolted joints in graphite/epoxy composite laminates. Composites Part B: Engineering, 2002, 33(7): 521-529.
[14] KOLKS G, TSERPES K I. Efficient progressive damage modeling of hybrid composite/titanium bolted joints. Composites Part A: Applied Science ＆ Manufacturing, 2014, 56(1): 51-63.
[15] HASHIN Z. Failure criteria for unidirectional fiber composites. Journal of Applied Mechanics, 1980, 47(2): 329-334.
[16] MCCARTHY 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. Composite Structures, 2005, 71(2): 140-158.