PSI - Issue 58

ScienceDirect Structural Integrity Procedia 00 (2023) 000–000 Structural Integrity Procedia 00 (2023) 000–000 Available online at www.sciencedirect.com Available online at www.sciencedirect.com ScienceDirect Available online at www.sciencedirect.com ScienceDirect

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

Procedia Structural Integrity 58 (2024) 42–47

7th International Conference on Structural Integrity and Durability (ICSID 2023) Fatigue life of damaged wing-fuselage fitting Aleksandar Grbovic a , Abdussalam Solob a , Zeljko Bozic b , Simon Sedmak c, *, Aleksandar Sedmak a,d 7th International Conference on Structural Integrity and Durability (ICSID 2023) Fatigue life of damaged wing-fuselage fitting Aleksandar Grbovic a , Abdussalam Solob a , Zeljko Bozic b , Simon Sedmak c, *, Aleksandar Sedmak a,d

a University of Belgrade, Faculty of Mechanical Engineering, Belgrade, Serbia b University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, Zagreb, Croatia c Innovation Center, Faculty of Mechanical Engineering, Kraljice Marije 16, 11000 Belgrade, Serbia d Transilvania University of Brasov, Faculty of Civil Engineering, Turnului st. 5, 500152 Bra ș ov, România a University of Belgrade, Faculty of Mechanical Engineering, Belgrade, Serbia b University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, Zagreb, Croatia c Innovation Center, Faculty of Mechanical Engineering, Kraljice Marije 16, 11000 Belgrade, Serbia d Transilvania University of Brasov, Faculty of Civil Engineering, Turnului st. 5, 500152 Bra ș ov, România

© 2024 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 ICSID 2023 Organizers Abstract Experimental analysis of full-scale wing was carried out for the purpose of numerical model verification. Comparisons of deformations measured and deformations calculated in FE simulations of aircraft wing deflection under load showed very good agreement, also confirming that loads acting on the wing-fuselage attachment lug were accurately evaluated in the analytical step. The detailed analysis has shown that the total maximum axial force transferred to lug by pin would be P ax,max = 208.83 kN, whereas the maximum transverse force would be P tr,max = 20.17 kN. © 2024 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 ICSID 2023 Organizers Keywords: Fatigue life; wing-fuselage fitting; full-scale testing 1. Introduction Fatigue life is one of the most important issues in aeronautical engineering, ever since fatal accidents with the first commercial jetliners DeHavilland almost seventy years ago, Solob, (2021). These unfortunate events initiated extensive research in leading laboratories at that time, which established new scientific discipline – fracture mechanics, and later on structural integrity, Sedmak et al, (2022). Even though these new disciplines are now in their mature state and can provide safe use of airplanes, certain problems with crack-like damage still exist, like in the wing-fuselage fitting, where cracks were found on the pickle forks in wing-fuselage attachment of Boeing 737NG jets before scheduled mandatory inspections, Boeing’s, (2023), The Guardian, (2023). Abstract Experimental analysis of full-scale wing was carried out for the purpose of numerical model verification. Comparisons of deformations measured and deformations calculated in FE simulations of aircraft wing deflection under load showed very good agreement, also confirming that loads acting on the wing-fuselage attachment lug were accurately evaluated in the analytical step. The detailed analysis has shown that the total maximum axial force transferred to lug by pin would be P ax,max = 208.83 kN, whereas the maximum transverse force would be P tr,max = 20.17 kN. © 2024 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 ICSID 2023 Organizers Keywords: Fatigue life; wing-fuselage fitting; full-scale testing 1. Introduction Fatigue life is one of the most important issues in aeronautical engineering, ever since fatal accidents with the first commercial jetliners DeHavilland almost seventy years ago, Solob, (2021). These unfortunate events initiated extensive research in leading laboratories at that time, which established new scientific discipline – fracture mechanics, and later on structural integrity, Sedmak et al, (2022). Even though these new disciplines are now in their mature state and can provide safe use of airplanes, certain problems with crack-like damage still exist, like in the wing-fuselage fitting, where cracks were found on the pickle forks in wing-fuselage attachment of Boeing 737NG jets before scheduled mandatory inspections, Boeing’s, (2023), The Guardian, (2023).

* Corresponding author. Tel.: +381-62-295-496. E-mail address: simon.sedmak@yahoo.com * Corresponding author. Tel.: +381-62-295-496. E-mail address: simon.sedmak@yahoo.com

2452-3216 © 2024 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 ICSID 2023 Organizers 2452-3216 © 2024 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 ICSID 2023 Organizers

2452-3216 © 2024 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 ICSID 2023 Organizers 10.1016/j.prostr.2024.05.008