期刊
FATIGUE & FRACTURE OF ENGINEERING MATERIALS & STRUCTURES
卷 41, 期 1, 页码 183-196出版社
WILEY
DOI: 10.1111/ffe.12671
关键词
2024-T3 aluminium alloy; compounding method; crack interaction; fatigue crack growth; multiple cracks; Stress Intensity Factor
资金
- European Commission in the context of the Fourth Framework Programme SMAAC - Structural Maintenance of Ageing Aircraft - Project [BRPR950079]
This article deals with the fatigue propagation of multiple cracks in finite width holed panels, which are typical of aircraft structural components. Theoretical studies in the literature have been considered and critically analyzed. Some of them have been translated into analytical models and implemented in a computer code. To check the effectiveness of the used models, a fatigue testing campaign has been conducted on six different configurations of notches and cracks. The comparison between experimental results and those obtained from the implemented models has shown a good agreement.
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