Original scientific paper

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

Abstract

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.

Keywords

Abaqus; aircraft spar; crack growth; fatigue life; stress intensity factor-SIF; XFEM

Hrčak ID:

86729

URI

https://hrcak.srce.hr/86729

Publication date:

19.9.2012.

Article data in other languages: croatian

Visits: 5.339 *