Vol.23, No.2, 2023, pp. 161–165


Aleksandar Grbović1*, Abdussalam Yousef Solob1, Simon Sedmak2, Aleksandar Sedmak1

1) University of Belgrade, Faculty of Mechanical Engineering, Belgrade, SERBIA

*email: agrbovic@mas.bg.ac.rs

2) University of Belgrade, Innovation Centre of the Faculty of Mechanical Engineering, Belgrade, SERBIA



Geometry of the wing-fuselage attachment lug was optimised using the fatigue life as the criterion geometry (thickness, hole radius, crack location). Numerical simulation of fatigue crack growth by XFEM was used to obtain fatigue life for different geometry parameters. The wing structure of the light aircraft was analysed first, and it was shown that it satisfies strength requirements according to standard CS23. Experimental verification of analytical/numerical results was carried out on the full-scale wing, and it was shown that differences between deformations are at a satisfactory low level. 

Keywords: lug, extended finite element method (XFEM), wing spar, fatigue life

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