期刊名称：International Journal of Innovative Research in Science, Engineering and Technology
印刷版ISSN：2347-6710
电子版ISSN：2319-8753
出版年度：2013
卷号：2
期号：7
页码：3330
出版社：S&S Publications
摘要：The current study includes a panel which represents the fuselage splice joint. The fuselage splice joint isa location where it experiences the uniform stress field at many rivet locations in a row. The probability of fatiguecracks initiation at many rivet locations simultaneously is more at splice joint. This paper has relevance in the structuralintegrity evaluation of aging transport aircrafts structural segment due to multisite damage.Finite element analysis ofthe Fuselage segment will be carried out to obtain the stress distribution near the joint. Fatigue cracks will emanatefrom the rivet holes simultaneously as they experience identical stresses due to internal pressure. In service the cracksin the fuselage will grow due to pressurization loading cycle (the difference in internal pressure and the atmosphericpressure at various altitudes). This study reveals the failure mechanics of the net section between the two advancingcrack tips.There are two competing mechanism of failure; Failure due to fracture and Failure due to net section yielding(plastic collapse). The mode of failure will depend on which of the above two occurs at a lower load. The stressintensity factor calculations are carried out by using Modified Virtual Crack Closure Integral (MVCCI) method. Thestress analysis is done using Nastran & Patran. The results were in compatible.
关键词：Fatigue; aircraft; Fuselage; Net section; Stress intensity factor; Finite element analysis
