Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels
2018
Аутори
Sghayer, AbulgasemGrbović, Aleksandar
Sedmak, Aleksandar
Dinulović, Mirko
Grozdanović, Ines
Sedmak, Simon
Petrovski, Blagoj
Чланак у часопису (Објављена верзија)
Метаподаци
Приказ свих података о документуАпстракт
Experimental and numerical analysis of fatigue crack growth in integral skin-stringer panels, produced by means of laser beam welding (LBW), is performed. Since this type of panel is used in airframe construction, fatigue and damage tolerance is of paramount importance, since aircrafts must be tolerant to relatively large fatigue cracks. Firstly, using extended finite element method (XFEM), the fatigue crack growth on the simple flat plate made of AL-AA 6156T6/ 2.8 mm was simulated, and results were compared with values obtained in the experiment. The same approach was taken to simulate the fatigue behaviour and crack propagation of the real skinstringer panel (four stringers, laser beam welded). It was found that the results obtained for stress intensity factors (SIFs) KI, KII, KIII and Keff along the crack front, are close to the experimental results, leading to conclusion that the XFEM method can be successfully used in prediction of fatigue life of complex airframe structures, such... as laserbeam welded skin-stringer panels.
Кључне речи:
XFEM / SIFs / integral skin-stringer structures / crack growth rateИзвор:
Tehnički vjesnik, 2018, 25, 3, 785-791Издавач:
- Univ Osijek, Tech Fac, Slavonski Brod
DOI: 10.17559/TV-20170308110329
ISSN: 1330-3651
WoS: 000437040900018
Scopus: 2-s2.0-85049369704
Институција/група
Inovacioni centarTY - JOUR AU - Sghayer, Abulgasem AU - Grbović, Aleksandar AU - Sedmak, Aleksandar AU - Dinulović, Mirko AU - Grozdanović, Ines AU - Sedmak, Simon AU - Petrovski, Blagoj PY - 2018 UR - https://machinery.mas.bg.ac.rs/handle/123456789/2758 AB - Experimental and numerical analysis of fatigue crack growth in integral skin-stringer panels, produced by means of laser beam welding (LBW), is performed. Since this type of panel is used in airframe construction, fatigue and damage tolerance is of paramount importance, since aircrafts must be tolerant to relatively large fatigue cracks. Firstly, using extended finite element method (XFEM), the fatigue crack growth on the simple flat plate made of AL-AA 6156T6/ 2.8 mm was simulated, and results were compared with values obtained in the experiment. The same approach was taken to simulate the fatigue behaviour and crack propagation of the real skinstringer panel (four stringers, laser beam welded). It was found that the results obtained for stress intensity factors (SIFs) KI, KII, KIII and Keff along the crack front, are close to the experimental results, leading to conclusion that the XFEM method can be successfully used in prediction of fatigue life of complex airframe structures, such as laserbeam welded skin-stringer panels. PB - Univ Osijek, Tech Fac, Slavonski Brod T2 - Tehnički vjesnik T1 - Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels EP - 791 IS - 3 SP - 785 VL - 25 DO - 10.17559/TV-20170308110329 ER -
@article{ author = "Sghayer, Abulgasem and Grbović, Aleksandar and Sedmak, Aleksandar and Dinulović, Mirko and Grozdanović, Ines and Sedmak, Simon and Petrovski, Blagoj", year = "2018", abstract = "Experimental and numerical analysis of fatigue crack growth in integral skin-stringer panels, produced by means of laser beam welding (LBW), is performed. Since this type of panel is used in airframe construction, fatigue and damage tolerance is of paramount importance, since aircrafts must be tolerant to relatively large fatigue cracks. Firstly, using extended finite element method (XFEM), the fatigue crack growth on the simple flat plate made of AL-AA 6156T6/ 2.8 mm was simulated, and results were compared with values obtained in the experiment. The same approach was taken to simulate the fatigue behaviour and crack propagation of the real skinstringer panel (four stringers, laser beam welded). It was found that the results obtained for stress intensity factors (SIFs) KI, KII, KIII and Keff along the crack front, are close to the experimental results, leading to conclusion that the XFEM method can be successfully used in prediction of fatigue life of complex airframe structures, such as laserbeam welded skin-stringer panels.", publisher = "Univ Osijek, Tech Fac, Slavonski Brod", journal = "Tehnički vjesnik", title = "Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels", pages = "791-785", number = "3", volume = "25", doi = "10.17559/TV-20170308110329" }
Sghayer, A., Grbović, A., Sedmak, A., Dinulović, M., Grozdanović, I., Sedmak, S.,& Petrovski, B.. (2018). Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels. in Tehnički vjesnik Univ Osijek, Tech Fac, Slavonski Brod., 25(3), 785-791. https://doi.org/10.17559/TV-20170308110329
Sghayer A, Grbović A, Sedmak A, Dinulović M, Grozdanović I, Sedmak S, Petrovski B. Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels. in Tehnički vjesnik. 2018;25(3):785-791. doi:10.17559/TV-20170308110329 .
Sghayer, Abulgasem, Grbović, Aleksandar, Sedmak, Aleksandar, Dinulović, Mirko, Grozdanović, Ines, Sedmak, Simon, Petrovski, Blagoj, "Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels" in Tehnički vjesnik, 25, no. 3 (2018):785-791, https://doi.org/10.17559/TV-20170308110329 . .