Fatigue life prediction method for hybrid multi-bolted joints based on damage weight

被引：0
|
作者：
Zhang J. [1 ,2 ]
Zheng X. [1 ,2 ]
Yuan L. [1 ,2 ]
Zhong G. [3 ]
Li G. [3 ]
机构：
[1] School of Aeronautics, Northwestern Polytechnical University, Xi'an
[2] Institute of Aircraft Composite Structures, Northwestern Polytechnical University, Xi'an
[3] AVIC Chengdu Aircraft Design & Research Institute, Chengdu
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2021年 / 42卷 / 05期
关键词：
Composite materials; Fatigue damage simulation; Fatigue life prediction; Layered damage detection; Multi-bolted joints;
D O I：
10.7527/S1000-6893.2020.24306
中图分类号：
学科分类号：
摘要：
The composite and metal material hybrid multi-bolted joints are the most common connection form in contemporary aircraft structures. Research on the fatigue performance of the hybrid multi-bolted joints helps to improve the understanding of the aircraft structure fatigue damage. A numerical analysis and an experimental study on the multi-nail connection structure of the ZT7H/QY9611 carbon fiber reinforced resin matrix composite plate and the 30CrMnSiNi2A metal plate with Ti-6Al-4V titanium alloy as bolts are conducted. The finite element method is used to predict the fatigue damage of the composite materials and fasteners, respectively, and simulate the damage near the nail holes on the composite material plate. An empirical formula with the distribution of fasteners and the number of layers of the composite material plate as parameters is proposed to accurately estimate the damage weight of the composite materials and fasteners, thereby effectively improving the accuracy of fatigue life prediction of hybrid multi-bolted joint structures. Through categorization and discussion of the damage patterns of nail holes based on the experimental results, the damage evolution of hybrid multi-nail connectors is explored; C-scan technology is adopted to detect layered damage of the composite materials which is compared with the simulation results to further verify the model. Compared with the experiment value, the logarithmic error of the life prediction simulation value considering the damage weight is only 1.1%, which is a significant increase from 8.4% of the method without considering the damage weight. © 2021, Beihang University Aerospace Knowledge Press. All right reserved.
引用
收藏
相关论文
共 20 条
  • [1] MAO H, MAHADEVAN S., Fatigue damage modelling of composite materials, Composite Structures, 58, 4, pp. 405-410, (2002)
  • [2] PLUMTREE A, SHEN G., Prediction of fatigue damage development in unidirectional long fibre composites, Polymers and Polymer Composites, 2, 2, pp. 83-90, (1994)
  • [3] EPAARACHCHI J A, CLAUSEN P D., A new cumulative fatigue damage model for glass fibre reinforced plastic composites under step/discrete loading, Composites Part A, 36, 9, pp. 1236-1245, (2005)
  • [4] WU F Q, YAO W X., A model of the fatigue life distribution of composite laminates based on their static strength distribution, Chinese Journal of Aeronautics, 21, 3, pp. 241-246, (2008)
  • [5] LIU J M, WAN X P, ZHAO M Y., Fatigue life prediction of laminated bolted joint structures, Acta Aeronautica et Astronautica Sinica, 36, 6, pp. 1867-1875, (2015)
  • [6] MARIAM M, AFENDI M, MAJID M S A, Et al., Tensile and fatigue properties of single lap joints of aluminium alloy/glass fibre reinforced composites fabricated with different joining methods, Composite Structures, 200, pp. 647-658, (2018)
  • [7] HART-SMITH L J., Mechanically-fastened joints for advanced composites-Phenomenological considerations and simple analyses, Fibrous Composites in Structural Design, pp. 543-574, (1980)
  • [8] YAN Y, WEN W D, CHANG F K, Et al., Experimental study on clamping effects on the tensile strength of composite plates with a bolt-filled hole, Composites Part A: Applied Science and Manufacturing, 30, 10, pp. 1215-1229, (1999)
  • [9] KRETSIS G, MATTHEWS F L., The strength of bolted joints in glass fibre/epoxy laminates, Composites, 16, 2, pp. 92-102, (1985)
  • [10] KAM C Y., Bolt hole growth in graphite-epoxy laminates for clearance and interference fits when subjected to fatigue loads, Fatigue of Fibrous Composite Materials, pp. 21-30, (1981)
12