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• W1603330451 abstract "Over the last few years considerable effort has been put into the improvement of the fatigue life of aircraft structures. Aircraft experience complex loading conditions during flight and safe operation requires understanding of the underlying mechanics of fatigue crack growth. One of the outcomes of the research carried out over the last thirty years is that fatigue cracks in metals are partially closed over part of a load cycle. This phenomenon is thought by many researchers to be the key to understanding the effect of non-uniform loading. Understanding crack closure is particularly challenging when initial residual stress fields (e.g. due to manufacturing or mechanical treatment) need to be taken into account. For example, rivet holes are a critical area for fatigue and they are usually cold expanded to create a beneficial residual stress field and to improve the fatigue performance. This paper describes the development of a simple analytical model for plasticity-i nduced fatigue crack closure taking into account the residual stresses due to cold expansion of rivet holes. The model is compared to a more sophisticated finite element analysis of plasticity-induced crack closure. The results show that the resi n dual stress field has a strong influence on the closure behaviour and therefore on fatigue crack propagation. The potential f for the application of this model to real components is assessed by modelling some experiments taken from the literature. The model results agree with the experimental findings for the location of fatigue crack initiation. Residual stresses from FE analyses of cold expansion were used as an input to the analytical closure model, which successfully predicted crack propagation from cold-expanded holes. The results obtained show that this approach has potential for use as a life prediction technique in design. RESUMO: Ao longo dos ultimos anos tem sido feito um esforco consideravel para melhorar a resistencia estrutural dos avioes a fenomenos de fadiga. Durante um voo os avioes sofrem condicoes de carga complexas, nestas condicoes para que o seu funcionamento seja seguro e necessario que se percebam os mecanismos fundamentais que governam a propagacao de fendas de fadiga. Um dos resultados da investigacao efectuada ao longo dos ultimos trinta anos indica que em metais as fendas estao parcialmente fechadas durante parte de um ciclo de carga. Muitos investigadores pensam que este fenomeno e a chave para se perceber o efeito de carregamentos nao uniformes. O fenomeno de crack closure e particularmente interessante quando se tem em consideracao a existencia de tensoes residuais (ex. devidas a processos de producao ou tratamentos mecânico). Como exemplo, os furos de rebites sao zonas criticas propicias a fenomenos de fadiga e sao usualmente expandidos para criar um campo de tensoes residuais para melhorar a sua resistencia a fadiga. Este artigo descreve o desenvolvimento de um modelo analitico simples para quantificar o fenomeno de crack closure induzido por plasticidade tendo em consideracao tensoes residuais devidas a expansao de furos de rebites. O modelo e comparado com analises de elementos finitos mais sofisticadas. Os resultados mostram que o campo de tensoes residuais tem uma influencia sigificativa no fenemeno de crack closure e consequentemente na propagacao de fendas de fadiga. A potencial aplicabilidade deste modelo em componentes reais e avaliado atraves da modelacao de trabalhos experimentais publicados na literatura. Os resultados obtidos com o modelo analitico estao em concordância com as observacoes experimentais no que diz respeito as zonas de inciacao das fendas. Os campos de tensoes residuais obtidos atraves de analises por elementos finitos foram usados como dados de entrada no modelo analitico de crack closure, que previu com sucesso a propagacao de fendas de fadiga a partir de furos expandidos. Os resultados mostram que esta tecnica tem potencial para ser usado em gabinetes de projecto. Palavras chave: Furos expandidos a frio, Tensoes residuais, Propagacao de fendas de fadiga, crack closure." @default.
• W1603330451 created "2016-06-24" @default.
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• W1603330451 date "2008-01-01" @default.
• W1603330451 modified "2023-09-24" @default.
• W1603330451 title "ANALYTICAL AND NUMERICAL MODELLING OF PLASTICITY-INDUCED FATIGUE CRACK CLOSURE NEAR COLD-EXPANDED HOLES IN AIRCRAFT STRUCTURES" @default.
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