Analysis of fatigue crack growth in an attachment lug based on the weight function technique and the UniGrow fatigue crack growth model

Mikheevskiy, S.; Glinka, G.; Algera, D.

doi:10.1016/j.ijfatigue.2011.07.006

Cited by 36 publications

(12 citation statements)

References 10 publications

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“…A comparison is done between the results of the WF and those in Ref. [14] for a lug with a quarter-circular crack subjected to a constant gross stress. Other approaches for simulating the pin loading are constant pressure and cosine pressure in the lug hole in the direction of pin load, which are also modeled in this work.…”

Section: Verification Of the Weight Functionmentioning

confidence: 99%

“…Wang [13] extracted a weight function (WF) for a wide range of through cracks in a lug based on the boundary element method. Mikheevskiy et al [14] employed the WF technique for fatigue crack growth analysis of a cracked lug using the load-shedding effect. The shape of crack changed from a quarter circular to an edge crack in the crack growth process of that quarter elliptical crack.…”

Section: Introductionmentioning

confidence: 99%

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Novel weight functions and stress intensity factors for quarterelliptical cracks in lug attachments

Akbari¹,

Nabavi

Moayeri³

2018

Frattura Ed Integrità Strutturale

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In this paper, a general weight function is developed to calculate the stress intensity factors (SIFs) for quarter-elliptical cracks in a wide range of lug attachment family. For this purpose, a series of finite element analyses are performed. Finally, using this unique extracted weight function, the influence of the pin loading model and crack parameters (aspect ratio and relative depth of the quarter-elliptical crack) on the SIFs is evaluated in the cracked lug attachments. The results of the present work are compared with some data available in the literature, and the agreement is satisfactory.

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Section: Verification Of the Weight Functionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Novel weight functions and stress intensity factors for quarterelliptical cracks in lug attachments

Akbari¹,

Nabavi

Moayeri³

2018

Frattura Ed Integrità Strutturale

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“…Since the lug joint is a sensitive and commonly used component in the aviation industry, the fatigue crack propagation of aircraft lug structure has been studied. [5][6][7][8] Papers 9,10 analyzed the failure of different joint lugs by using fracture mechanics parameters, while 11,12 focused on the microstructure of such failure. Based on the results of finite element analysis, Ekvall et al established the relationship between the elastic stress concentration factor Kt and the lug geometry.…”

Section: Introductionmentioning

confidence: 99%

Effects of different structural parameters on the 7075-T651 aluminum alloy lug structure fatigue life

Wang

Huang

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Lug structure is an important connection structure in aviation aircraft. However, fatigue cracks are easily generated during the service of the aircraft. Therefore, this study aims to explore the influence of different structural parameters on the fatigue life of the 7075-T651 aluminum alloy lug, using experimental and numerical methods to determine the effects of these structural parameters. Scanning electron microscopy was employed for fracture analysis, and three-dimensional finite element models were used to solve the holes edge stress distributions under peak load and stress concentration factor. The results indicate that the fatigue life of the lug increases with the increase in the extrusion projection area and the included angle of the outer edge, and the impact of the extrusion projection area on the fatigue life of the lug is greater than the angle of the outer edge, and the fatigue life of the lug does not change with the change of the chamfer at the bottom. The peak stress at the root of the lug hole becomes the main factor affecting the fatigue life of the lug, and the crack always expands along the net cross-section of each parameter lug.

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“…Design and sustainment activities require analysis of these connections using stress intensity factor (SIF) solutions to relate the loading, geometry, and crack size to the driving force for fatigue and fracture. Consequently, the literature contains many references [1][2][3][4][5] to analyses of cracks originating at the pinhole interface. However, the SIF solutions are themselves depend on the underlying assumptions of the analyst.…”

Section: Introductionmentioning

confidence: 99%

Modelling considerations for stress intensity factor solutions at pin‐loaded holes

Sobotka

McClung

2019

Fatigue Fract Eng Mat Struct

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This work summarizes investigations into stress intensity factor solutions for straight, through cracks at pin‐loaded holes in thin sheets. As shown in this work, several assumptions contribute to the fidelity of a stress intensity factor solution that includes the distribution of contact pressure on the pin‐hole interface, the friction coefficient at the pin‐hole interface, the crack initiation angle, and stiffness mismatch. These assumptions lead to higher or lower stress intensity factor solutions as demonstrated by results generated from advanced finite element analyses of the relevant geometries. Results shown here contribute to the development of a realistic and conservative set of assumptions for stress intensity factor solutions. Conclusions drawn from this work are applicable to cracks originating at pin‐loaded holes in plates and lugs.

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Analysis of fatigue crack growth in an attachment lug based on the weight function technique and the UniGrow fatigue crack growth model

Cited by 36 publications

References 10 publications

Novel weight functions and stress intensity factors for quarterelliptical cracks in lug attachments

Novel weight functions and stress intensity factors for quarterelliptical cracks in lug attachments

Effects of different structural parameters on the 7075-T651 aluminum alloy lug structure fatigue life

Modelling considerations for stress intensity factor solutions at pin‐loaded holes

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