不同激光冲击区域对7075铝合金结构件缺口疲劳性能的影响

殷之平; 陈瑶; 黎泽松; 郭挺

doi:10.13433/j.cnki.1003-8728.20200546

不同激光冲击区域对7075铝合金结构件缺口疲劳性能的影响

doi: 10.13433/j.cnki.1003-8728.20200546

1.
西北工业大学民航学院，西安　710072
2.
陕西千山航空电子有限责任公司，西安　710072

详细信息

作者简介:
殷之平（1977−），副教授，硕士生导师，博士，研究方向为疲劳与断裂，yzp@nwpu.edu.cn

中图分类号: V215.2⁺5
计量
- 文章访问数: 116
- HTML全文浏览量: 73
- PDF下载量: 15
- 被引次数: 0
出版历程
- 收稿日期: 2021-01-14
- 网络出版日期: 2023-02-16
- 刊出日期: 2022-12-05

Effects of Different Laser Impact Regions on Fatigue Performance of Structural Parts of 7075 Aluminum Alloy

1.
School of Civil Aviation, Northwestern Polytechnical University, Xi′an 710072, China
2.
Shaanxi Qianshan Avionics Co., Ltd., Xi′an 710072, China

摘要

摘要: 为了探究不同激光冲击区域对铝合金板材缺口的疲劳性能的影响，对7075-T651合金板材结构的缺口的不同区域进行了激光冲击处理。第1种方法仅针对板材的缺口边缘进行激光冲击；第2种方法是在板材缺口的一定范围内进行激光冲击。结果表明：采用第1种激光冲击方法，板材表面粗糙度更小，且板材的特征疲劳寿命是第2种激光冲击方法的3.23倍。通过对激光冲击的板材进行有限元仿真分析，揭示了激光冲击强化对板材疲劳寿命影响的原因。只有设置合理的激光冲击参数与冲击区域才能有效地改善疲劳性能，提升结构的疲劳寿命，不合理的冲击处理方式反而会降低结构的疲劳寿命。
- 7050-T651铝合金 /
- 缺口 /
- 激光冲击区域 /
- 粗糙度 /
- 疲劳寿命 /
- 有限元仿真
Abstract: In order to explore the influence of the different laser impact areas on the fatigue performance of aluminum alloy plate notched, the effect of the laser impact treatment on the different areas of 7075-T651 alloy plate structure notchedis conducted. The first method is laser impact only on the edge of the gap, and the second method is laser impact within a certain range of the gap. The results show that the surface roughness of the plate is smaller and the characteristic fatigue life of the plate is 3.23 times than that of the second laser impact method. Through the finite element simulation analysis of the plate subjected the laser impact, the reason of the laser impact on the fatigue life of the plate was revealed. Only to set the reasonable laser impact parameters and impact area will effectively improve the fatigue performance and the fatigue life of the structure be will increase, while the unreasonable impact treatment will reduce the fatigue life of the structure.
- 7050-T651 /
- notch /
- laser impact region /
- roughness /
- fatigue life /
- finite element simulation

HTML全文

图 1 激光加工强化过程示意图

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图 2 7075-T651铝合金板材试样

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图 3 激光冲击强化区域

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图 4 MTS-250疲劳试验机

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图 5 两种冲击方法疲劳寿命对比

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图 6 7075-T651铝合金试件表面形貌

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图 7 7075-T651铝合金板材疲劳断口

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图 8 激光冲击路径及光斑搭接率

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图 9 有限元模型边界及网格划分

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图 10 不同Path路径

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图 11 不同峰值压力下粗糙度

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图 12 激光冲击数值模拟应力云图

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图 13 沿着厚度方向应力分布

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表 1 7075-T651铝合金化学成分^[19]

Si	Fe	Cu	Zn	其余元素	Al
0.4	0.5	1.2~2.0	5.1~6.1	7.38~9.28	余量

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表 2 未强化的7075-T651铝合金板材疲劳试验数据

试验件编号	试验最大载荷 P_max/kN	应力比 r	频率 f/Hz	疲劳寿命 N/Cycle
NLSP-1	8.5	0.1	20	99504
NLSP-2	8.5	0.1	20	168505
NLSP-3	8.5	0.1	20	142897
NLSP-4	8.5	0.1	20	151236
NLSP-5	8.5	0.1	20	126886

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表 3 强化后7075-T651铝合金板材的疲劳试验结果（强化区域a）

试验件编号	试验最大载荷 P_max/kN	应力比 r	频率 f/Hz	预寿命+剩余疲劳寿命N/Cycle
LSP-1a	8.5	0.1	20	71500+248443
LSP-2a	8.5	0.1	20	71500+710123
LSP-3a	8.5	0.1	20	71500+554637
LSP-4a	8.5	0.1	20	71500+184130
LSP-5a	8.5	0.1	20	71500+214701

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表 4 强化后7075-T651铝合金板材的疲劳试验结果（强化区域b）

试验件编号	试验最大载荷P_max/kN	应力比 r	频率 f/Hz	预寿命+剩余疲劳寿命N/Cycle	寿命增益/%
LSP-1b	8.5	0.1	20	71500+177244	−22.25
LSP-2b	8.5	0.1	20	71500+10749	−89.47
LSP-3b	8.5	0.1	20	71500+43682	−81.6
LSP-4b	8.5	0.1	20	71500+65055	−46.58
LSP-5b	8.5	0.1	20	71500+86728	−44.71

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表 5 7075-T7651材料Johnson-Cook模型参数^[24]

A/MPa	B/MPa	C	n
336.5	342.7	0.01	0.43

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