Version 1
: Received: 27 August 2024 / Approved: 27 August 2024 / Online: 27 August 2024 (13:43:26 CEST)
How to cite:
Zichil, V.; Grigoras, C. C.; Ciubotariu, V. A. Induced Scratches and Fatigue in Aircraft-Grade Aluminium Alloys. A Statistical Analysis on the UTS and Elongation at Break. Preprints2024, 2024081962. https://doi.org/10.20944/preprints202408.1962.v1
Zichil, V.; Grigoras, C. C.; Ciubotariu, V. A. Induced Scratches and Fatigue in Aircraft-Grade Aluminium Alloys. A Statistical Analysis on the UTS and Elongation at Break. Preprints 2024, 2024081962. https://doi.org/10.20944/preprints202408.1962.v1
Zichil, V.; Grigoras, C. C.; Ciubotariu, V. A. Induced Scratches and Fatigue in Aircraft-Grade Aluminium Alloys. A Statistical Analysis on the UTS and Elongation at Break. Preprints2024, 2024081962. https://doi.org/10.20944/preprints202408.1962.v1
APA Style
Zichil, V., Grigoras, C. C., & Ciubotariu, V. A. (2024). Induced Scratches and Fatigue in Aircraft-Grade Aluminium Alloys. A Statistical Analysis on the UTS and Elongation at Break. Preprints. https://doi.org/10.20944/preprints202408.1962.v1
Chicago/Turabian Style
Zichil, V., Cosmin Constantin Grigoras and Vlad Andrei Ciubotariu. 2024 "Induced Scratches and Fatigue in Aircraft-Grade Aluminium Alloys. A Statistical Analysis on the UTS and Elongation at Break" Preprints. https://doi.org/10.20944/preprints202408.1962.v1
Abstract
The present study analyses the influence of scratches and fatigue on the mechanical characteristics of aluminium alloys commonly used in the aviation industry: 2024-T4, 6061-T4, 6061-T4 uncoated, 6061-T6 uncoated, 7075-T0, and 7076-T6. 120 specimens were used for the study. Out of these, 60 samples were scratched, and the other 60 samples were also scratched under the same circumstances and then 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 mechanical properties of both scratched and scratched-fatigued sample sets. The LCF pre-treatment contributes to the negative impacts of scratches, resulting in a reduced value for the ultimate tensile strength and elongation at break. The results conclude that surface integrity plays an essential role in preserving aircraft components' structural strength.
Copyright:
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
