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Fatigue crack growth in fiber-metal laminates

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  • Special Topic: Airworthiness and Fatigue
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Abstract

Fiber-metal laminates (FMLs) consist of three layers of aluminum alloy 2024-T3 and two layers of glass/epoxy prepreg, and it (it means FMLs) 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 monolithic 2024-T3 Al alloy plates. It is shown that the fatigue life of FMLs is about 17 times longer than monolithic 2024-T3 Al alloy plate; and crack growth rates in FMLs panels remain constant mostly even when the crack is long, unlike in the monolithic 2024-T3 Al alloy plates. The formula to calculate bridge stress profiles of FMLs was derived based on the fracture theory. A program by Matlab was developed to calculate the distribution of bridge stress in FMLs, and then fatigue growth lives were obtained. Finite element models of FMLs were built and meshed finely to analyze the stress distributions. Both results were compared with the experimental results. They agree well with each other.

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Authors and Affiliations

  1. School of Aeronautics, Northwestern Polytechnical University, Xi’An, 710072, China

    YuE Ma & ZhongChun Xia

  2. AVIC Chengdu Aircraft Design & Research Institute, ChengDu, 610041, China

    XiaoFeng Xiong

Authors
  1. YuE Ma
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  2. ZhongChun Xia
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  3. XiaoFeng Xiong
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Correspondence to YuE Ma.

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Ma, Y., Xia, Z. & Xiong, X. Fatigue crack growth in fiber-metal laminates. Sci. China Phys. Mech. Astron. 57, 83–89 (2014). https://doi.org/10.1007/s11433-013-5336-6

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  • DOI: https://doi.org/10.1007/s11433-013-5336-6

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