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航空级铝合金的缺口与疲劳

Notches and Fatigue on Aircraft-Grade Aluminium Alloys.

作者信息

Zichil Valentin, Grigoras Cosmin Constantin, Ciubotariu Vlad Andrei

机构信息

Department of Engineering and Management, Mechatronics, "Vasile Alecsandri" University of Bacău, 157 Calea Mărăsesti, 600115 Bacau, Romania.

Department of Industrial Systems Engineering and Management, "Vasile Alecsandri" University of Bacău, 157 Calea Mărăsesti, 600115 Bacau, Romania.

出版信息

Materials (Basel). 2024 Sep 21;17(18):4639. doi: 10.3390/ma17184639.

DOI:10.3390/ma17184639
PMID:39336380
原文链接:https://pmc.ncbi.nlm.nih.gov/articles/PMC11433727/
Abstract

The influence of notches and fatigue on the ultimate tensile strength and elongation at break of aluminium alloys (2024-T3, 6061-T4, 6061-T4 uncoated, 6061-T6 uncoated, 7075-T0, and 7076-T6) is presented in this study. A total of 120 specimens were used. On all specimens, notches were made using a CNC machine, with 60 of them subjected to low-cycle fatigue (LCF) before undergoing the tensile test. Based on the statistical examination of the measured data, mathematical prediction models have been established. Compared to their unscratched counterparts, the results indicate a significant decrease in the UTS and elongation at break for both notched and notched-fatigued specimens. The LCF pre-treatment contributes to the negative impacts of the notches, resulting in reduced values for the UTS and elongation at break, thus concluding that surface integrity is critical for maintaining the structural strength of aircraft components.

摘要

本研究展示了缺口和疲劳对铝合金（2024-T3、6061-T4、6061-T4未涂层、6061-T6未涂层、7075-T0和7076-T6）的极限抗拉强度和断裂伸长率的影响。总共使用了120个试样。在所有试样上，使用数控机床制作缺口，其中60个在进行拉伸试验前承受低周疲劳（LCF）。基于对测量数据的统计检验，建立了数学预测模型。结果表明，与未划痕的对应试样相比，有缺口和有缺口且经疲劳处理的试样的极限抗拉强度和断裂伸长率均显著降低。低周疲劳预处理加剧了缺口的负面影响，导致极限抗拉强度和断裂伸长率值降低，从而得出表面完整性对于维持飞机部件的结构强度至关重要的结论。

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