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<p>A286 superalloy blind rivets are critical fasteners in aircraft structural connections, and the fatigue strength of their joints is a key factor in ensuring operational safety. Despite their importance, research on the fatigue behavior of riveted joints and the effects of rivet installation processes remains limited. In this study, macroscopic failure modes and microscopic mechanisms of riveted joints under fatigue loading were investigated using pull-pull fatigue tests and scanning electron microscopy (SEM). Fatigue life predictions were performed through simulations in Abaqus and FE-Safe, including a quantitative analysis of the effects of sheet thickness and hole diameter on joint fatigue strength. Macroscopically, the failure mode is characterized by a fracture at the rivet’s contact arc segment. Microscopically, fatigue cracks initiate at the outer surface of this segment and propagate radially inward as intergranular fractures, subsequently shifting along a circumferential path around the rivet bulge, ultimately leading to complete rivet fracture. The fatigue strength of the riveted joints first increases and then decreases with increasing interlayer thickness or decreasing hole diameter. Notably, the failure location transitions from the contact arc segment to the sleeve head under these variations. This study provides a theoretical basis for improving the structural safety and durability of aircraft components.</p>

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Fatigue Failure Mechanisms and Life Prediction of A286 Superalloy Blind Rivets in Riveted Joints under Tension-Tension Cyclic Loading

  • 期刊论文

  • 发表日期：

    2026年1月9日

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  • Shiwen Tang,
  • Zhiguo Feng,
  • Liang Tao,
  • Yulian Jiang,
  • Yongjin Wu

摘要

A286 superalloy blind rivets are critical fasteners in aircraft structural connections, and the fatigue strength of their joints is a key factor in ensuring operational safety. Despite their importance, research on the fatigue behavior of riveted joints and the effects of rivet installation processes remains limited. In this study, macroscopic failure modes and microscopic mechanisms of riveted joints under fatigue loading were investigated using pull-pull fatigue tests and scanning electron microscopy (SEM). Fatigue life predictions were performed through simulations in Abaqus and FE-Safe, including a quantitative analysis of the effects of sheet thickness and hole diameter on joint fatigue strength. Macroscopically, the failure mode is characterized by a fracture at the rivet’s contact arc segment. Microscopically, fatigue cracks initiate at the outer surface of this segment and propagate radially inward as intergranular fractures, subsequently shifting along a circumferential path around the rivet bulge, ultimately leading to complete rivet fracture. The fatigue strength of the riveted joints first increases and then decreases with increasing interlayer thickness or decreasing hole diameter. Notably, the failure location transitions from the contact arc segment to the sleeve head under these variations. This study provides a theoretical basis for improving the structural safety and durability of aircraft components.