Research On Fatigue Property Of Riveted Component For Aircraft Fuselage

Riveting is widely used in aircraft structure assembly. The stress concentration of riveting makesit become weak section. So the fatigue performance of riveting component has direct influence on thesecurity and reliability of aircraft service. Reasonable interference fit could improve the fatigueperformance, therefore the interference fit technology could be used in riveting. This paper studied thefatigue performance of riveting component through process control. It has a great significance for thereliable connection of aircraft fuselage structure. The research mainly includes as follows:Firstly, the existing process to improve fatigue resistance of connection is analyzed. This papercompares the advantages and disadvantages from cost, weight and so on, and proposes that theriveting interference fit technology is more suitable for aircraft fuselage connection. The fatiguesstrengthen mechanism for riveting interference fit is perspectives from elastic-plastic mechanics andfracture mechanics. The key process factors that effect fatigue strength is studied.Secondly, this paper introduces the finite element technology for riveted process is necessary andfeasible. The three-dimensional riveting component model is built through finite element software. Toanalysis the characteristics of material flow the riveting deformation is simulated. In order to ensurethe reliability of subsequent analysis results, the accuracy of model is verified through comparing thesize of riveted head with riveted experiment. The influence of key process factors on riveting qualityis analyzed from hole deformation and stress distribution. At last the paper gives process controlindicators for riveted quality.Thirdly, the fatigue limit for single riveted component is determined through static loadexperiment. So as to determine fatigue load spectrum. This paper also studies the stress distributioncharacteristics, the method of load transfer and failure mechanism under the action of static load. Themaximum principal stress distribution in different riveted height and hole’s precision is discussed. Theinfluence of these factors on fatigue crack initiation location is analyzed. The fatigue life of rivetedcomponents is predicted by use of fatigue simulation system based on stress results in finite elementstatic analysis. The fatigue simulation results were verified through fatigue experiment.It is a reference for our country’s large civil aircraft automatic drilling and riveting processstandard through the above research.