FEM based fatigue crack growth predictions for spar of light aircraft under variable amplitude loading
Само за регистроване кориснике
2012
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In the last decades, the assessment of the service durability of aerospace components and assemblies has become an important segment of design, mostly because of the growing needs for the light-weight structures which will be safe and reliable, and at the same time, not too expensive. It is especially true for the main structural elements such as wing spar, fuselage bulkheads and fittings, whose sudden failure could lead to the catastrophic consequences. In order to meet the strict safety requirements, as well as to check structural components before usage, a number of expensive and long experiments are carried out. Taking into account ever-present manufacturer tendencies to shorten time-to-market periods, the use of finite element method (FEM) for the estimation of fatigue life has been proved as a good alternative to the experimental methods. The purpose of this article is to show that it is possible, by using finite element analysis (FEA), to obtain not only the good estimation of t...he fatigue life of the assembly such as the spar of the light aircraft, but also a good prediction of a number of load cycles which will propagate a crack on the spar to a certain length. On the basis of these results, it is possible to determine the proper inspections intervals which could prevent the catastrophic failure of the aircraft structure under variable amplitude loading.
Кључне речи:
FEM / Fatigue / Failure / Crack / AircraftИзвор:
Engineering Failure Analysis, 2012, 26, 50-64Издавач:
- Pergamon-Elsevier Science Ltd, Oxford
DOI: 10.1016/j.engfailanal.2012.07.003
ISSN: 1350-6307
WoS: 000313843700006
Scopus: 2-s2.0-84865817399
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Институција/група
Mašinski fakultetTY - JOUR AU - Grbović, Aleksandar AU - Rašuo, Boško PY - 2012 UR - https://machinery.mas.bg.ac.rs/handle/123456789/1519 AB - In the last decades, the assessment of the service durability of aerospace components and assemblies has become an important segment of design, mostly because of the growing needs for the light-weight structures which will be safe and reliable, and at the same time, not too expensive. It is especially true for the main structural elements such as wing spar, fuselage bulkheads and fittings, whose sudden failure could lead to the catastrophic consequences. In order to meet the strict safety requirements, as well as to check structural components before usage, a number of expensive and long experiments are carried out. Taking into account ever-present manufacturer tendencies to shorten time-to-market periods, the use of finite element method (FEM) for the estimation of fatigue life has been proved as a good alternative to the experimental methods. The purpose of this article is to show that it is possible, by using finite element analysis (FEA), to obtain not only the good estimation of the fatigue life of the assembly such as the spar of the light aircraft, but also a good prediction of a number of load cycles which will propagate a crack on the spar to a certain length. On the basis of these results, it is possible to determine the proper inspections intervals which could prevent the catastrophic failure of the aircraft structure under variable amplitude loading. PB - Pergamon-Elsevier Science Ltd, Oxford T2 - Engineering Failure Analysis T1 - FEM based fatigue crack growth predictions for spar of light aircraft under variable amplitude loading EP - 64 SP - 50 VL - 26 DO - 10.1016/j.engfailanal.2012.07.003 ER -
@article{ author = "Grbović, Aleksandar and Rašuo, Boško", year = "2012", abstract = "In the last decades, the assessment of the service durability of aerospace components and assemblies has become an important segment of design, mostly because of the growing needs for the light-weight structures which will be safe and reliable, and at the same time, not too expensive. It is especially true for the main structural elements such as wing spar, fuselage bulkheads and fittings, whose sudden failure could lead to the catastrophic consequences. In order to meet the strict safety requirements, as well as to check structural components before usage, a number of expensive and long experiments are carried out. Taking into account ever-present manufacturer tendencies to shorten time-to-market periods, the use of finite element method (FEM) for the estimation of fatigue life has been proved as a good alternative to the experimental methods. The purpose of this article is to show that it is possible, by using finite element analysis (FEA), to obtain not only the good estimation of the fatigue life of the assembly such as the spar of the light aircraft, but also a good prediction of a number of load cycles which will propagate a crack on the spar to a certain length. On the basis of these results, it is possible to determine the proper inspections intervals which could prevent the catastrophic failure of the aircraft structure under variable amplitude loading.", publisher = "Pergamon-Elsevier Science Ltd, Oxford", journal = "Engineering Failure Analysis", title = "FEM based fatigue crack growth predictions for spar of light aircraft under variable amplitude loading", pages = "64-50", volume = "26", doi = "10.1016/j.engfailanal.2012.07.003" }
Grbović, A.,& Rašuo, B.. (2012). FEM based fatigue crack growth predictions for spar of light aircraft under variable amplitude loading. in Engineering Failure Analysis Pergamon-Elsevier Science Ltd, Oxford., 26, 50-64. https://doi.org/10.1016/j.engfailanal.2012.07.003
Grbović A, Rašuo B. FEM based fatigue crack growth predictions for spar of light aircraft under variable amplitude loading. in Engineering Failure Analysis. 2012;26:50-64. doi:10.1016/j.engfailanal.2012.07.003 .
Grbović, Aleksandar, Rašuo, Boško, "FEM based fatigue crack growth predictions for spar of light aircraft under variable amplitude loading" in Engineering Failure Analysis, 26 (2012):50-64, https://doi.org/10.1016/j.engfailanal.2012.07.003 . .