航空学报 > 2022, Vol. 43 Issue (1): 224811-224811   doi: 10.7527/S1000-6893.2020.24811

铝合金薄板冲击后疲劳试验与谱载寿命

张亦波1, 陈迪2, 成正强2, 沈培良1, 熊峻江2   

  1. 1. 上海飞机设计研究院 机体集成部, 上海 201210;
    2. 北京航空航天大学 交通科学与工程学院, 北京 100083
  • 收稿日期:2020-09-29 修回日期:2020-11-30 出版日期:2022-01-15 发布日期:2020-11-27
  • 通讯作者: 张亦波 E-mail:zhangyibo@comac.cc
  • 基金资助:
    国家自然科学基金(51875021)

Fatigue experiments and lifetime for post-impact sheets of aluminum-alloys(AAs) under block spectrum loading

ZHANG Yibo1, CHEN Di2, CHENG Zhengqiang2, SHEN Peiliang1, XIONG Junjiang2   

  1. 1. Airframe Integration Department, Shanghai Aircraft Design and Research Institute, Shanghai 201210, China;
    2. School of Transportation Science and Engineering, Beihang University, Beijing 100083, China
  • Received:2020-09-29 Revised:2020-11-30 Online:2022-01-15 Published:2020-11-27
  • Supported by:
    National Natural Science Foundation of China(51875021)

摘要: 对航空铝合金2524-T3和7075-T62薄板分别进行了4种不同冲击能量的低速冲击试验,并对冲击后薄板进行了静力拉伸、恒幅加载疲劳性能及块谱加载疲劳寿命试验,研究了冲击凹坑尺寸(或冲击能量)对静力性能、疲劳强度以及疲劳寿命的影响;根据断口形貌和试验观察,分析和讨论了冲击对疲劳特性和损伤机理的影响。为估算冲击后薄板谱载疲劳寿命,在试验基础上提出新的冲击后薄板疲劳性能S-N-Kt表征模型,采用新模型处理试验数据,得到的理论结果与试验数据吻合良好。基于Johnson-Cook本构方程,建立了冲击后铝合金薄板的非线性弹塑性有限元模型,模拟了冲击凹坑附近的残余应力和应力集中;利用冲击后薄板疲劳性能S-N-Kt模型,预测了冲击后的航空铝合金2524-T3和7075-T62薄板的块谱疲劳寿命,预测结果和试验数据吻合良好,精度可接受。

关键词: 疲劳, 低速冲击, 铝合金薄板, 寿命, 块谱加载

Abstract: Tests of low velocity impact are performed on the sheets of AAs 2524-T3 and 7075-T62, respectively, with four different impact forces, and static and fatigue experiments are conducted on the intact and post-impact sheets under static tensile, constant amplitude and block spectrum loading. The impact-dent size, static and fatigue properties, and spectrum-loading life are determined, with the effect of impact on fatigue characteristics and damage mechanism analyzed and discussed from fractographic and experimental observations. An S-N-Kt surface model is proposed to depict fatigue characteristics for fatigue lifetime prediction of post-impact sheets subjected to block spectrum loading. A new concept is applied for experimental data and a reasonable agreement obtained between the theoretical and experimental results, demonstrating the effective and practical use of the developed surface model. A nonlinear elastic-plastic FE model based on the Johnson-Cook constitutive equation is generated to model the residual stress patterns and stress concentration around the impact-dent, and fatigue lives of post-impact sheets of AAs 2524-T3 and 7075-T62 subjected to block spectrum loading are predicted from the S-N-Kt surface model. Good agreements have been achieved between predictions and experiments.

Key words: fatigue, low velocity impact, aluminum-alloy sheet, lifetime, block spectrum loading

中图分类号: