铝合金薄板冲击后疲劳试验与谱载寿命

doi:10.7527/S1000-6893.2020.24811

固体力学与飞行器总体设计

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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. 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. 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/Abstract

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-K_t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-K_t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-K_t 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-K_t 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:

V216.3

张亦波, 陈迪, 成正强, 沈培良, 熊峻江. 铝合金薄板冲击后疲劳试验与谱载寿命[J]. 航空学报, 2022, 43(1): 224811-224811.

ZHANG Yibo, CHEN Di, CHENG Zhengqiang, SHEN Peiliang, XIONG Junjiang. Fatigue experiments and lifetime for post-impact sheets of aluminum-alloys(AAs) under block spectrum loading[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 224811-224811.

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铝合金薄板冲击后疲劳试验与谱载寿命

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

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