Tehnički vjesnik, Vol. 19 No. 3, 2012.
Izvorni znanstveni članak
Extended finite element method (XFEM) applied to aircraft duralumin spar fatigue life estimation
Danilo Petrašinović
; University of Belgrade, Faculty of Mechanical Engineering, Kraljice Marije 16, Belgrade, Serbia
Boško Rašuo
orcid.org/0000-0002-0912-6844
; University of Belgrade, Faculty of Mechanical Engineering, Kraljice Marije 16, Belgrade, Serbia
Nikola Petrašinović
; University of Belgrade, Faculty of Mechanical Engineering, Kraljice Marije 16, Belgrade, Serbia
Sažetak
In the present work, duralumin aircraft spar fatigue life is evaluated by extended finite element method (XFEM) under cyclic loading condition. The effect of the crack growth on the fatigue life of aircraft spar is discussed in detail. The values of stress intensity factors (SIFs) are extracted from the XFEM solution. Standard Paris fatigue crack growth law (currently, the only one incorporated in Abaqus) is used for the fatigue life estimation. Obtained results are compared with previously obtained experimental results.
Ključne riječi
Abaqus; aircraft spar; crack growth; fatigue life; stress intensity factor-SIF; XFEM
Hrčak ID:
86729
URI
Datum izdavanja:
19.9.2012.
Posjeta: 5.305 *