XFEM based analysis of fatigue crack growth in damaged wing-uselage attachment lug
Само за регистроване кориснике
2020
Чланак у часопису (Објављена верзија)
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Приказ свих података о документуАпстракт
The research presented in this paper is based on the use of extended finite element method (XFEM) for stress intensity factors (SIFs) determination in the case of fatigue crack presented in the wing-fuselage attachment lug used in light aerobatic aircraft. The presence of the through crack at the attachment lug hole is not allowed since its growth due to high dynamic loads is usually fast and can lead to catastrophic consequences. To demonstrate how dangerous the appearance of the crack could be, as well as to estimate the residual strength and fatigue life of cracked component, finite element model of attachment lug was made, and analyses were carried out using the maximum load that can occur during the flight (load factor n = 6). The predicted number of cycles to complete failure was - as expected - low, confirming the fact that attachment lugs must be designed using safe-life approach.
Кључне речи:
XFEM / Wing-fuselage attachment lug / Light aerobatic aircraft / Fatigue crack growthИзвор:
Engineering Failure Analysis, 2020, 112Издавач:
- Pergamon-Elsevier Science Ltd, Oxford
DOI: 10.1016/j.engfailanal.2020.104516
ISSN: 1350-6307
WoS: 000539308100001
Scopus: 2-s2.0-85082836724
Институција/група
Inovacioni centarTY - JOUR AU - Solob, A. AU - Grbović, Aleksandar AU - Bozić, Z. AU - Sedmak, Simon PY - 2020 UR - https://machinery.mas.bg.ac.rs/handle/123456789/3393 AB - The research presented in this paper is based on the use of extended finite element method (XFEM) for stress intensity factors (SIFs) determination in the case of fatigue crack presented in the wing-fuselage attachment lug used in light aerobatic aircraft. The presence of the through crack at the attachment lug hole is not allowed since its growth due to high dynamic loads is usually fast and can lead to catastrophic consequences. To demonstrate how dangerous the appearance of the crack could be, as well as to estimate the residual strength and fatigue life of cracked component, finite element model of attachment lug was made, and analyses were carried out using the maximum load that can occur during the flight (load factor n = 6). The predicted number of cycles to complete failure was - as expected - low, confirming the fact that attachment lugs must be designed using safe-life approach. PB - Pergamon-Elsevier Science Ltd, Oxford T2 - Engineering Failure Analysis T1 - XFEM based analysis of fatigue crack growth in damaged wing-uselage attachment lug VL - 112 DO - 10.1016/j.engfailanal.2020.104516 ER -
@article{ author = "Solob, A. and Grbović, Aleksandar and Bozić, Z. and Sedmak, Simon", year = "2020", abstract = "The research presented in this paper is based on the use of extended finite element method (XFEM) for stress intensity factors (SIFs) determination in the case of fatigue crack presented in the wing-fuselage attachment lug used in light aerobatic aircraft. The presence of the through crack at the attachment lug hole is not allowed since its growth due to high dynamic loads is usually fast and can lead to catastrophic consequences. To demonstrate how dangerous the appearance of the crack could be, as well as to estimate the residual strength and fatigue life of cracked component, finite element model of attachment lug was made, and analyses were carried out using the maximum load that can occur during the flight (load factor n = 6). The predicted number of cycles to complete failure was - as expected - low, confirming the fact that attachment lugs must be designed using safe-life approach.", publisher = "Pergamon-Elsevier Science Ltd, Oxford", journal = "Engineering Failure Analysis", title = "XFEM based analysis of fatigue crack growth in damaged wing-uselage attachment lug", volume = "112", doi = "10.1016/j.engfailanal.2020.104516" }
Solob, A., Grbović, A., Bozić, Z.,& Sedmak, S.. (2020). XFEM based analysis of fatigue crack growth in damaged wing-uselage attachment lug. in Engineering Failure Analysis Pergamon-Elsevier Science Ltd, Oxford., 112. https://doi.org/10.1016/j.engfailanal.2020.104516
Solob A, Grbović A, Bozić Z, Sedmak S. XFEM based analysis of fatigue crack growth in damaged wing-uselage attachment lug. in Engineering Failure Analysis. 2020;112. doi:10.1016/j.engfailanal.2020.104516 .
Solob, A., Grbović, Aleksandar, Bozić, Z., Sedmak, Simon, "XFEM based analysis of fatigue crack growth in damaged wing-uselage attachment lug" in Engineering Failure Analysis, 112 (2020), https://doi.org/10.1016/j.engfailanal.2020.104516 . .