PSI - Issue 28

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Procedia Structural Integrity 28 (2020) 124–131

1st Virtual European Conference on Fracture -VECF1 Aircraft Fuselage Cracking and Simulation A.M. Al-Mukhtar a,* a Al-Hussain University College, Iraq a Institute of Structural Mechanics, Bauhaus‐Universität Weimar, Germany 1st Virtual European Conference on Fracture -VECF1 Aircraft Fuselage Cracking and Simulation A.M. Al-Mukhtar a,* a Al-Hussain University College, Iraq a Institute of Structural Mechanics, Bauhaus‐Universität Weimar, Germany

© 2020 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of the European Structural Integrity Society (ESIS) ExCo © 2020 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the VCSI1 organizers Abstract The atigue failure is predomina e in aircraft fuselage. The fuselage ski consists of the shell and stingers. Fatigue plays a ig i icant role in the cr ck growth of the skin stru tures. T er mai tenance and scheduled test intervals may avoid sudden skin failure and crack path (CP). With xiting th c acks, the propagation rate incre ses dramatically. Ther fore, shortening t regular inspection inte vals is recommended. Ne rtheless, the young mac ines may have also unexpected ski upture. The cracks are manating from th otches such as riv ts and the holes under the cyclic l ading. The stresses concentrated around these notches. The stress concentration provid the uniqu condition for crack initiation. Therefor , the cra ks tend to connect with each other. Hence, the number of cycles to failure is decreased dramat cally. Although the last decades, the fractu toughness, design, and new alloying element are enhanced. According to the traditional fuselage failure, the crack inspections are recommended even after a few thousand cycles. © 2020 The Authors. Published by Elsevier B.V. This is an ope acces article under C BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Abstract The fatigue failure is predominate in the aircraft fuselage. The fuselage skin consists of the shell and stingers. Fatigue plays a significant role in the crack growth of the skin structures. The proper maintenance and scheduled test intervals may avoid sudden skin failure and crack path (CP). With exiting the cracks, the propagation rate increases dramatically. Therefore, shortening the regular inspection intervals is recommended. Nevertheless, the young machines may have also unexpected skin rupture. The cracks are emanating from the notches such as rivets and the holes under the cyclic loading. The stresses concentrated around these notches. The stress concentration provides the unique conditions for crack initiation. Therefore, the cracks tend to connect with each other. Hence, the number of cycles to failure is decreased dramatically. Although the last decades, the fracture toughness, design, and new alloying element are enhanced. According to the traditional fuselage failure, the crack inspections are recommended even after a few thousand cycles. 1. Introduction The airplane fuselage consists of skin or metal shells and stringers (see Fig. 1a). They provide a massive cylindrical structure. The semi-monocoque design is used for the fuselage since it carries more loads and providing the rigidity. Fatigue in terms of the repeated loads initiates the crack. The propagation into a critical crack size causes a sudden failure. The crack initiates from the notches like defects, welds, and rivets due to the concentration 1. Introduction The airplane fuselag consists f skin or metal hells and stringers (see Fig. 1a). They provide a mass ve cylindr cal structur . The semi-monocoque design i used for fuselage since it carr es more loads and provid ng the rigidity. Fatigue in terms of the rep ated loads initiates th crack. Th propagation into a critical rack s ze causes a sudden failure. The crack initiates from the notches like defects, welds, and rivets due to the concentration Keywords: Airplane; Crack; Crack path; Fracture; Fuselage; Stress concentration Peer-review under responsibility of the VCSI1 organizers Keywords: Airplane; Crack; Crack path; Fracture; Fuselage; Stress concentration

* Corresponding author. Tel.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail address: almukhtar@hotmail.de * Corresponding author. Tel.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail address: almukhtar@hotmail.de

2452-3216 © 2020 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the VCSI1 organizers 2452-3216 © 2020 The Authors. Published by Elsevier B.V. This is an ope access article under t C BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/) Peer-review under responsibility of the VCSI1 organizers

2452-3216 © 2020 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of the European Structural Integrity Society (ESIS) ExCo 10.1016/j.prostr.2020.10.016