Add to ORKGIn 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
In this chapter, FEM is used for fatigue crack growth predictions on 2D model of the spar, whereas X...
V magistrskem delu smo predstavili uporabo komercialnega programa Abaqus 6.12 za napoved rasti razpo...
AbstractPredicting fatigue crack growth (FCG) rate and path under variable amplitude loading (VAL) i...
U ovom radu prikazano je određivanje zamornog vijeka duraluminijske ramenjače aviona primjenom proši...
This paper presents the application of the extended finite element method (XFEM) in crack propagatio...
The assessment of the service durability of aerospace components and assemblies has become an import...
This paper presents an application of the extended finite element method (XFEM) to the modelling of ...
Fatigue cracks growth in three different wing spar geometries is simulated using xFEM, as the most s...
Dobra procena zamorne izdržljivosti vazduhoplovnih komponenti i sklopova je poslednjih decenija post...
In the last decades, the assessment of the service durability of aerospace components and assemblies...
Shape optimisation is a nowadays-standard requirement in the design of lightweight structural compon...
The work presents a numerical and experimental analysis of a full-scale fatigue test on a CFRP rear ...
Based on the theory of linear elastic fracture mechanics, the relationships between material constan...
Different cracks paths in three different wing spar designs are analysed (differential, integral and...
The research presented in this paper is based on the use of extended finite element method (XFEM) fo...
In this chapter, FEM is used for fatigue crack growth predictions on 2D model of the spar, whereas X...
V magistrskem delu smo predstavili uporabo komercialnega programa Abaqus 6.12 za napoved rasti razpo...
AbstractPredicting fatigue crack growth (FCG) rate and path under variable amplitude loading (VAL) i...
U ovom radu prikazano je određivanje zamornog vijeka duraluminijske ramenjače aviona primjenom proši...
This paper presents the application of the extended finite element method (XFEM) in crack propagatio...
The assessment of the service durability of aerospace components and assemblies has become an import...
This paper presents an application of the extended finite element method (XFEM) to the modelling of ...
Fatigue cracks growth in three different wing spar geometries is simulated using xFEM, as the most s...
Dobra procena zamorne izdržljivosti vazduhoplovnih komponenti i sklopova je poslednjih decenija post...
In the last decades, the assessment of the service durability of aerospace components and assemblies...
Shape optimisation is a nowadays-standard requirement in the design of lightweight structural compon...
The work presents a numerical and experimental analysis of a full-scale fatigue test on a CFRP rear ...
Based on the theory of linear elastic fracture mechanics, the relationships between material constan...
Different cracks paths in three different wing spar designs are analysed (differential, integral and...
The research presented in this paper is based on the use of extended finite element method (XFEM) fo...
In this chapter, FEM is used for fatigue crack growth predictions on 2D model of the spar, whereas X...
V magistrskem delu smo predstavili uporabo komercialnega programa Abaqus 6.12 za napoved rasti razpo...
AbstractPredicting fatigue crack growth (FCG) rate and path under variable amplitude loading (VAL) i...