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Technical gazette, Vol. 25 No. 3, 2018.

Original scientific paper

https://doi.org/10.17559/TV-20170308110329

Experimental and Numerical Analysis of Fatigue Crack Growth in Integral Skin-Stringer Panels

Abulgasem Sghayer ; University of Belgrade, Faculty of Mechanical Engineering, Kraljice Marije 16, 11120 Belgrade, Serbia
Aleksandar Grbović orcid id orcid.org/0000-0001-9525-4270 ; University of Belgrade, Faculty of Mechanical Engineering, Kraljice Marije 16, 11120 Belgrade, Serbia
Aleksandar Sedmak orcid id orcid.org/0000-0002-5438-1895 ; University of Belgrade, Faculty of Mechanical Engineering, Kraljice Marije 16, 11120 Belgrade, Serbia
Mirko Dinulović ; University of Belgrade, Faculty of Mechanical Engineering, Kraljice Marije 16, 11120 Belgrade, Serbia
Ines Grozdanović ; University of Belgrade, Faculty of Mining and geology, Djusina 7, 11000 Belgrade, Serbia
Simon Sedmak orcid id orcid.org/0000-0002-2674-541X ; Innovation Center of Faculty of Mechanical Engineering, Kraljice Marije 16, 11120 Belgrade, Serbia
Blagoj Petrovski ; Innovation Center of Faculty of Mechanical Engineering, Kraljice Marije 16, 11120 Belgrade, Serbia

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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 skin-stringer 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 laser-beam welded skin-stringer panels.

Keywords

crack growth rate; integral skin-stringer structures; SIFs; XFEM

Hrčak ID:

202621

URI

https://hrcak.srce.hr/202621

Publication date:

28.6.2018.

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