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| Naji, M. |
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| Motta, Antonella |
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| Aletan, Dirar |
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| Mohamed, Tarek |
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| Ertürk, Emre |
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| Taccardi, Nicola |
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| Kononenko, Denys |
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| Petrov, R. H. | Madrid |
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| Alshaaer, Mazen | Brussels |
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| Bih, L. |
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| Casati, R. |
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| Muller, Hermance |
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| Kočí, Jan | Prague |
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| Šuljagić, Marija |
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| Kalteremidou, Kalliopi-Artemi | Brussels |
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| Azam, Siraj |
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| Ospanova, Alyiya |
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| Blanpain, Bart |
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| Ali, M. A. |
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| Popa, V. |
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| Rančić, M. |
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| Ollier, Nadège |
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| Azevedo, Nuno Monteiro |
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| Landes, Michael |
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| Rignanese, Gian-Marco |
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Breitbarth, Eric
in Cooperation with on an Cooperation-Score of 37%
Topics
Publications (10/10 displayed)
- 2024An iterative crack tip correction algorithm discovered by physical deep symbolic regressioncitations
- 2024Numerical Simulations of Stress Intensity Factors and Fatigue Life in L-Shaped Sheet Profilescitations
- 2024Next generation fatigue crack growth experiments of aerospace materialscitations
- 2023Werkstoffmechanische Prüfung der nächsten Generation: Rissfortschritt komplexer Rumpfstrukturen
- 2023Strategies to accelerate the design, discovery, development and deployment of materials in the era of the digital transformation
- 2023Fatigue crack growth in anisotropic aluminium sheets–phase-field modelling and experimental validationcitations
- 2022Towards three dimensional aspects of plasticity-induced crack closure: A finite element simulationcitations
- 2022Damage Mechanisms and Anisotropy of an AA7010-T7452 Open-Die Forged Alloy: Fatigue Crack Propagationcitations
- 2020High-stress fatigue crack propagation in thin AA2024-T3 sheet materialcitations
- 2019Anisotropes Rissausbreitungsverhalten einer freiformgeschmiedeten, hochfesten AA7010-T7652 Legierung
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article
High-stress fatigue crack propagation in thin AA2024-T3 sheet material
Abstract
Fatigue crack growth in 1.6‐mm‐thick sheets of aluminium alloy AA2024‐T3 was investigated under very high‐stress conditions using 950‐mm‐wide middle tension (MT) specimens. Experiments were conducted by applying uniaxial load ratios R (0.1, 0.3 and 0.5) with the maximum nominal stress of 120 MPa following conditions relevant for aircraft fuselage structures. The experiments were conducted with digital image correlation to determine loading conditions acting on the crack tip. Stable crack growth rates of up to da/dN > 4 mm/cycle and ΔK > 100 MPa√m were reached, and final crack lengths 2a > 500 mm were obtained. High‐stress intensity factors cause plastic zone sizes that extend up to approximately 100 mm from the crack tip. The da/dN‐ΔK data obtained in this study provide crucial information about the fatigue crack growth and damage tolerance of very long cracks under high‐stress conditions in thin lightweight structures.