Effects of hole reaming on fatigue performance of thin sheets for fuselage: DIC and FEM analysis

Yajun Chen; Jinchuan Yang; Changtian Zhang; Fusheng Wang; Chunming Ji

doi:10.1016/j.ijfatigue.2020.105893

Effects of hole reaming on fatigue performance of thin sheets for fuselage: DIC and FEM analysis

Yajun Chen^*
, Jinchuan Yang
, Changtian Zhang
, Fusheng Wang
, Chunming Ji

^*Corresponding author for this work

Civil Aviation University of China

Research output: Contribution to journal › Article › peer-review

13 Scopus citations

Abstract

The effects of hole reaming (HR) after pre-fatigue damage on fatigue performance of AA2198-T8 were studied by using the digital image correlation (DIC) technique. The influences of stress distribution of the rivet hole on fatigue life were studied. When maximum axial strain is equal to 0.0005, the number of fatigue cycles is suggested as the fatigue crack initiation life. The prediction of fatigue lives by the calculation method combining Paris law and ABAQUS, and the experimental results are within a factor of 1.2-scatter band. This work provides a reference for the maintenance of fatigue damaged rivet holes in aircraft structure.

Original language	English
Article number	105893
Journal	International Journal of Fatigue
Volume	141
DOIs	https://doi.org/10.1016/j.ijfatigue.2020.105893
State	Published - Dec 2020
Externally published	Yes

Keywords

Aluminum-lithium alloy
Digital image correlation
Fatigue life prediction
Finite element method
Hole reaming

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10.1016/j.ijfatigue.2020.105893

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@article{af7ec414a3ea4fa4b31aecb6f96c039f,

title = "Effects of hole reaming on fatigue performance of thin sheets for fuselage: DIC and FEM analysis",

abstract = "The effects of hole reaming (HR) after pre-fatigue damage on fatigue performance of AA2198-T8 were studied by using the digital image correlation (DIC) technique. The influences of stress distribution of the rivet hole on fatigue life were studied. When maximum axial strain is equal to 0.0005, the number of fatigue cycles is suggested as the fatigue crack initiation life. The prediction of fatigue lives by the calculation method combining Paris law and ABAQUS, and the experimental results are within a factor of 1.2-scatter band. This work provides a reference for the maintenance of fatigue damaged rivet holes in aircraft structure.",

keywords = "Aluminum-lithium alloy, Digital image correlation, Fatigue life prediction, Finite element method, Hole reaming",

author = "Yajun Chen and Jinchuan Yang and Changtian Zhang and Fusheng Wang and Chunming Ji",

note = "Publisher Copyright: {\textcopyright} 2020 Elsevier Ltd",

year = "2020",

month = dec,

doi = "10.1016/j.ijfatigue.2020.105893",

language = "英语",

volume = "141",

journal = "International Journal of Fatigue",

issn = "0142-1123",

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}

TY - JOUR

T1 - Effects of hole reaming on fatigue performance of thin sheets for fuselage

T2 - DIC and FEM analysis

AU - Chen, Yajun

AU - Yang, Jinchuan

AU - Zhang, Changtian

AU - Wang, Fusheng

AU - Ji, Chunming

PY - 2020/12

Y1 - 2020/12

N2 - The effects of hole reaming (HR) after pre-fatigue damage on fatigue performance of AA2198-T8 were studied by using the digital image correlation (DIC) technique. The influences of stress distribution of the rivet hole on fatigue life were studied. When maximum axial strain is equal to 0.0005, the number of fatigue cycles is suggested as the fatigue crack initiation life. The prediction of fatigue lives by the calculation method combining Paris law and ABAQUS, and the experimental results are within a factor of 1.2-scatter band. This work provides a reference for the maintenance of fatigue damaged rivet holes in aircraft structure.

AB - The effects of hole reaming (HR) after pre-fatigue damage on fatigue performance of AA2198-T8 were studied by using the digital image correlation (DIC) technique. The influences of stress distribution of the rivet hole on fatigue life were studied. When maximum axial strain is equal to 0.0005, the number of fatigue cycles is suggested as the fatigue crack initiation life. The prediction of fatigue lives by the calculation method combining Paris law and ABAQUS, and the experimental results are within a factor of 1.2-scatter band. This work provides a reference for the maintenance of fatigue damaged rivet holes in aircraft structure.

KW - Aluminum-lithium alloy

KW - Digital image correlation

KW - Fatigue life prediction

KW - Finite element method

KW - Hole reaming

UR - https://www.scopus.com/pages/publications/85089492109

U2 - 10.1016/j.ijfatigue.2020.105893

DO - 10.1016/j.ijfatigue.2020.105893

M3 - 文章

AN - SCOPUS:85089492109

SN - 0142-1123

VL - 141

JO - International Journal of Fatigue

JF - International Journal of Fatigue

M1 - 105893

ER -

Effects of hole reaming on fatigue performance of thin sheets for fuselage: DIC and FEM analysis

Abstract

Keywords

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