Effect of the countersunk rivet head dimensions on fatigue behavior of riveted specimens of 2024-T3 alloy
Aircraft Engineering and Aerospace Technology
ISSN: 0002-2667
Article publication date: 27 August 2024
Issue publication date: 30 September 2024
Abstract
Purpose
This study aims to investigate the effect of countersunk rivet head dimensions on the fatigue performance of the riveted specimens of 2024-T3 alloy.
Design/methodology/approach
The relationship between rivet head dimensions and fatigue behavior was investigated by finite element method and fatigue test. The fatigue fracture of the specimens was analyzed by scanning electron microscopy.
Findings
A change of the rivet head dimensions will cause a change in the stress concentration and residual normal stress, the stress concentration near the rivet hole causes the fatigue crack source to be located on the straight section of the countersunk rivet hole and the residual normal stress can effectively restrain the initiation and expansion of fatigue cracks. The fatigue cycle will cause the rivet holes to produce different degrees of surface wear.
Originality/value
The fatigue life of the specimens with the height of the rivet head of 2.28 mm and 2.00 mm are similar, but the specimens with the height of the rivet head of 1.72 mm were far higher than the other specimens.
Keywords
Acknowledgements
The work was supported by the National Natural Science Foundation of China (Grant No. 12272090) and the Opening fund of State Key Laboratory of Nonlinear Mechanics. Special thanks are due to the instrumental analysis from Analytical and Testing Center, Northeastern University.
Declaration of interests: The authors declare that they have no known competing financial interests or personal relationships that could have appeared to influence the work reported in this paper.
Citation
Lv, G., Jia, D., Li, C., Zhao, C., Zhang, X., Yan, F., Zhang, H. and Li, B. (2024), "Effect of the countersunk rivet head dimensions on fatigue behavior of riveted specimens of 2024-T3 alloy", Aircraft Engineering and Aerospace Technology, Vol. 96 No. 9, pp. 1181-1191. https://doi.org/10.1108/AEAT-02-2024-0051
Publisher
:Emerald Publishing Limited
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