Abstract Much of the structural loading in an aircraft is transferred through fuselage skin panels to riveted fastening holes at lap joint of these panels. Stress concentration caused by these fastening holes lead to a large loading of cycle tensile stress on these holes, and then bring in fatigue fracture. According to statistics, fatigue fracture of fastening holes accounts for 90% of the whole fatigue fracture of the aircraft, which becomes the main cause of aircraft structure failure. It is a significant research on how to reduce effects of stress concentration to improve aircraft anti-fatigue in design material and manufacture. In this chapter, how to determine the effects of hole surface quality to the stress distribution and life of aluminum perforated panel by finite element software and test are introduced.
Effect of Surface Quality of Open Holes on Fatigue Life
2018-01-01
31 pages
Article/Chapter (Book)
Electronic Resource
English
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