Fatigue crack growth in fiber-metal laminates
Fiber-metal laminates (FMLs) consist of three layers of aluminium alloy 2024-T3 and two layers glass/epoxy prepreg,and it is laminated by Al alloy and fiber alternatively.Fatigue crack growth rates in notched fiber-metal laminates under constant amplitude fatigue loading were studied experimentally and numerically and were compared with them in Al alloy 2024-T3 plates.It is shown that fatigue live of FMLs is about 17 times longer than Al alloy 2024-T3 plate;and crack growth rates in FMLs panels keep the same value mostly even when the crack is long,not like in Al alloy 2024-T3.The formula to calculate bridge stress profiles of FMLs were derived based on the fracture theory.A program by Matlab was made to calculate the distribution of bridge stress in FMLs,and then fatigue lives were obtained.Finite element models of FMLs were built and meshed finely to analyze the stress distributiom.Both results were compared with the experiment results.They agree well with each other.
fiber metal laminates fatigue crack growth bridge stress fatigue life
Y.E.Ma Z.C.Xia X.F.Xiong
School of Aeronautics,Northwestern Polytechnical University,Xian 710072,China AVIC Chengdu Aircraft Design & Research Institute,Chengdu 610041,China
国际会议
International Conference on Airworthiness & Fatigue -7th ICSAELS Series Conference(大飞机安全性能与疲劳国际会议)
北京
英文
95-99
2013-03-24（万方平台首次上网日期，不代表论文的发表时间）