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Journal of Engineering Materials and Technology | Volume 139 | Issue 2 | research-article
Research Papers

Fatigue Damage Analysis of Double-Lap Bolted Joints Considering the Effects of Hole Cold Expansion and Bolt Clamping Force

[+] Author and Article Information
Ying Sun, Qingchun Meng, Yuanming Xu

School of Aeronautics Science and Engineering,
Beihang University,
Beijing 100191, China

George Z. Voyiadjis

Computational Solid Mechanics Laboratory,
Department of Civil and Environmental
Engineering,
Louisiana State University,
Baton Rouge, LA 70803

Weiping Hu

School of Aeronautics Science and Engineering,
Beihang University,
Room D604, New Main Building,
37th Xueyuan Road,
Beijing 100191, China;Computational Solid Mechanics Laboratory,
Department of Civil and Environmental
Engineering,
Louisiana State University,
Baton Rouge, LA 70803
e-mail: huweiping@buaa.edu.cn

1Corresponding author.

Contributed by the Materials Division of ASME for publication in the JOURNAL OF ENGINEERING MATERIALS AND TECHNOLOGY. Manuscript received May 31, 2016; final manuscript received September 13, 2016; published online February 7, 2017. Assoc. Editor: Taehyo Park.

J. Eng. Mater. Technol 139(2), 021007 (Feb 07, 2017) (10 pages) Paper No: MATS-16-1157; doi: 10.1115/1.4035325 History: Received May 31, 2016; Revised September 13, 2016
Article
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Hole cold expansion and bolt clamping force are usually applied to improve the fatigue performance of bolted joints. In order to investigate the effects of hole cold expansion and bolt clamping force and reveal the mechanism of these two factors on the fatigue damage of bolted joint, a continuum damage mechanics (CDM) based approach in conjunction with the finite element method is used. The damage-coupled Voyiadjis plasticity constitutive model is used to represent the material behavior, which is implemented by user material subroutine in abaqus. The elasticity and plasticity damage evolutions of the material are described by the stress-based and plastic-strain-based equations, respectively. The fatigue damage of joint is calculated using abaqus cycle by cycle. The fatigue lives of double-lap bolted joints with and without clamping force at different levels of hole cold expansion are all obtained. The characteristics of fatigue damage corresponding to the different conditions are presented to unfold the influencing mechanism of these two factors. The predicted fatigue lives and crack initiation locations are in good agreement with the experimental results available in the literature. The beneficial effects of hole cold expansion and bolt clamping force on the fatigue behavior of bolted joint are presented in this work.
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References

Figures

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Fig. 1

Stress-strain curve for Al alloy 2024-T3

+Stress-strain curve for Al alloy 2024-T3
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Stress-strain curve for Al alloy 2024-T3
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Fig. 2

Fatigue life comparison between the integrated NLCD and SWT model

+Fatigue life comparison between the integrated NLCD and SWT model
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Fatigue life comparison between the integrated NLCD and SWT model
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Fig. 3

(a) Dimensions of assembled bolted joint specimens [36], and tapered pins used for hole cold expansion of (b) 1.5% and (c) 4.7% [31]

+(a) Dimensions of assembled bolted joint specimens [36], and tapered pins used for hole cold expansion of (b) 1.5% and (c) 4.7% [31]
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(a) Dimensions of assembled bolted joint specimens [36], and tapered pins used for hole cold expansion of (b) 1.5% and (c) 4.7% [31]
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Fig. 4

Finite element model of the bolted joint specimen

+Finite element model of the bolted joint specimen
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Finite element model of the bolted joint specimen
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Fig. 5

Simplified algorithm of the numerical simulation

+Simplified algorithm of the numerical simulation
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Simplified algorithm of the numerical simulation
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Fig. 6

The predicted fatigue lives calculated by (a) proposed approach and (b) SWT method versus the experimental results[6]

+The predicted fatigue lives calculated by (a) proposed approach and (b) SWT method versus the experimental results[6]
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The predicted fatigue lives calculated by (a) proposed approach and (b) SWT method versus the experimental results[6]
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Fig. 7

Predicted damage field and fatigue crack nucleation locations for different bolted joints

+Predicted damage field and fatigue crack nucleation locations for different bolted joints
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Predicted damage field and fatigue crack nucleation locations for different bolted joints
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Fig. 8

Experimental fatigue crack nucleation location for different bolted joints [6]

+Experimental fatigue crack nucleation location for different bolted joints [6]
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Experimental fatigue crack nucleation location for different bolted joints [6]
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Fig. 10

Predicted and experimental fatigue lives versus tightening torque for the bolted joints with hole cold expansion level of (a) 0% and (b) 1.5%

+Predicted and experimental fatigue lives versus tightening torque for the bolted joints with hole cold expansion level of (a) 0% and (b) 1.5%
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Predicted and experimental fatigue lives versus tightening torque for the bolted joints with hole cold expansion level of (a) 0% and (b) 1.5%
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Fig. 9

Predicted and experimental fatigue lives versus hole cold expansion level for bolted joint clamped with (a) 0 N·m and (b) 4 N·m

+Predicted and experimental fatigue lives versus hole cold expansion level for bolted joint clamped with (a) 0 N·m and (b) 4 N·m
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Predicted and experimental fatigue lives versus hole cold expansion level for bolted joint clamped with (a) 0 N·m and (b) 4 N·m
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Fig. 11

Longitudinal stresses σX at the critical location for different bolted joints clamped with tightening torques of (a) 0 N·m and (b) 4 N·m

+Longitudinal stresses σX at the critical location for different bolted joints clamped with tightening torques of (a) 0 N·m and (b) 4 N·m
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Longitudinal stresses σX at the critical location for different bolted joints clamped with tightening torques of (a) 0 N·m and (b) 4 N·m
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Fig. 12

Stress-strain curve of integration points at crack nucleation location for different bolted joints: (a) 0% and 0 N·m, (b) 1.5% and 0 N·m, (c) 4.7% and 0 N·m, (d) 0% and 4 N·m, (e) 1.5% and 4 N·m, and (f) 4.7% and 4 N·m

+Stress-strain curve of integration points at crack nucleation location for different bolted joints: (a) 0% and 0 N·m, (b) 1.5% and 0 N·m, (c) 4.7% and 0 N·m, (d) 0% and 4 N·m, (e) 1.5% and 4 N·m, and (f) 4.7% and 4 N·m
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Stress-strain curve of integration points at crack nucleation location for different bolted joints: (a) 0% and 0 N·m, (b) 1.5% and 0 N·m, (c) 4.7% and 0 N·m, (d) 0% and 4 N·m, (e) 1.5% and 4 N·m, and (f) 4.7% and 4 N·m

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