7B04-T6铝合金腐蚀疲劳交替寿命预测模型

李昌范; 何宇廷; 张胜; 李旭; 杜旭; 张腾

doi:10.13224/j.cnki.jasp.2016.05.007

7B04-T6铝合金腐蚀疲劳交替寿命预测模型

doi: 10.13224/j.cnki.jasp.2016.05.007

1. 空军工程大学航空航天工程学院, 西安 710038;
2. 中国人民解放军 94578部队, 江苏盐城 224000

基金项目:

国家自然科学基金(51475470)

详细信息

作者简介:
李昌范(1986-),男,河南民权人,博士生,主要从事飞机结构可靠性与安全性研究.

中图分类号: V216.3
计量
- 文章访问数: 1038
- HTML浏览量: 3
- PDF量: 650
- 被引次数: 0
出版历程
- 收稿日期: 2016-01-10
- 刊出日期: 2016-05-28

Life prediction model of 7B04-T6 aluminum alloy under alternate action of corrosion and fatigue

1. Aeronautic and Astronautic Engineering College, Air Force Engineering University, Xi'an 710038, China;
2. Unite 94578, the Chinese People's Liberation Army, Yancheng Jiangsu 224000, China

摘要

摘要: 利用7B04-T6铝合金进行了预腐蚀试验和"腐蚀+疲劳+腐蚀+疲劳+……"交替模式作用下的腐蚀疲劳交替试验.试验结果表明:在腐蚀疲劳交替作用下,试验件寿命比相同腐蚀时间作用下的预腐蚀试验件寿命长.利用试验结果建立了基于损伤力学和非线性损伤累积理论的腐蚀疲劳交替寿命预测模型.提出了利用损伤指数描述腐蚀损伤和疲劳损伤在交替过程中的耦合关系,并分析了损伤指数变化对模型迟滞因子和模型预测精度的影响.通过模型分析,在腐蚀疲劳交替过程中,疲劳加载次数对寿命的影响大于腐蚀时间的影响,并且随着加载次数增加试验件的寿命也增加.
- 腐蚀疲劳交替 /
- 迟滞因子 /
- 非线性损伤累积理论 /
- 损伤指数 /
- 寿命预测模型
Abstract: The alternate test of corrosion and fatigue and pre-corrosion test were carried out on 7B04-T6 aluminum alloy. The test results showed that the life of alternate test in sequence of "corrosion+fatigue+corrosion+fatigue+……" was longer than pre-corrosion test under the same corrosion time. According to the test results, the life prediction model of alternate action corrosion and fatigue was built based on the theory of damage mechanics and nonlinear damage cumulative theory. The damage exponent described the relationship of corrosion damage and the fatigue damage of the alternate action of corrosion and fatigue. The effects of damage exponent on precision and hysteretic factor of the model were discussed. Fatigue cycles had more serious effect on the total life than the corrosion time in the progress of alternation action of corrosion and fatigue. The total life got longer with the increase of fatigue cycles.
- alternate action of corrosion and fatigue /
- hysteretic factor /
- nonlinear damage cumulative theory /
- damage exponent /
- life prediction model

HTML

参考文献(19)

[1]	Walde K V,Hillberry B M.Initiation and shape of development of corrosion-nucleated fatigue cracking[J].International Journal of Fatigue,2007,29(7):1269-1281.
[2]	Sriaman M R,Pidapati R M.Life prediction of aircraft aluminum subjected to pitting corrosion under fatigue condition[J].Journal of Aircraft,2009,46(4):1253-1259.
[3]	Akid R,Dmytrakh I.Influence of surface deformation and electron chemical variables on corrosion and corrosion fatigue crack development[J].Fatigue and Fracture of Engineering Materials and Structures,1998,21(7):903-911.
[4]	刘文珽,李玉海.飞机结构日历寿命体系评定技术[M].北京.航空工业出版社,2004.
[5]	李玉海,刘文珽.腐蚀条件下飞机结构疲劳寿命评定技术研究[J].飞机设计,2002(4):1-10. LI Yuhai,LIU Wenting.Study on assessing fatigue life of aircraft strictures under corrosion environment[J].Aircraft Design,2002(4):1-10.(in Chinese)
[6]	贺小帆,刘文珽,蒋东滨.一种考虑腐蚀影响的飞机结构疲劳试验方法[J].北京航空航天大学学报,2003,29(1):20-22. HE Xiaofan,LIU Wenting,JIANG Dongbin.Method of fatigue test of aircraft structures considering corrosion influence[J].Journal of Beijing University of Aeronautics and Astronautics,2003,29(1):20-22.(in Chinese)
[7]	陈群志,陈志伟,刘文珽,等.腐蚀环境下飞机结构日历寿命研究现状与关键技术问题[J].中国安全科学学报,2000,10(3):43-47. CHEN Qunzhi,CHEN Zhiwei,LIU Wenting,et.al.Research situation and key technology of calendar life of aircraft structure under corrosion environment[J].China Safety Science Journal,2000,10(3):43-47.(in Chinese)
[8]	陈群志,杨瑞琴,李国元,等.腐蚀对30CrMnSiNi2A钢结构疲劳寿命的影响[J].装备环境工程,2007,4(5):7-9,17. CHEN Qunzhi,YANG Ruiqin,LI Guoyuan,et al.Influence of corrosion on fatigue life of 30CrMnSiNi2A steel structure[J].Equipment Environment Engineering,2007,4(5):7-9,17.(in Chinese)
[9]	杨晓华,姚卫星,段成美.腐蚀环境下LC4铝合金疲劳损伤累积规律研究[J].航空学报,2003,24(3):234-236. YANG Xiaohua,YAO Weixing,DUAN Chengmei.Research on fatigue damage cumulative rule under corrosion environment[J].Acta Aeronautics et Astronautics Sinica,2003,24(3):234-236.(in Chinese)
[10]	杨晓华.腐蚀累积损伤理论研究与飞机结构日历寿命分析[D].南京:南京航空航天大学,2002. YANG Xiaohua.Study on corrosion cumulative damage rules and the calendar life of aircraft structures[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2002.(in Chinese)
[11]	陈跃良,卞贵学,衣林,等.腐蚀和疲劳交替作用下飞机铝合金疲劳性能及断裂机理研究[J].机械工程学报,2012,48(20):70-76. CHEN Yueliang,BIAN Guixue,YI Lin,et al.Research on fatigue characteristic and fracture mechanics of aluminum alloy under alternate action of corrosion and fatigue[J].Journal of Mechanical Engineering,2012,48(20):70-76.(in Chinese)
[12]	Du M L,Chiang F,Kagwade S,et al.Damage of Al2024 alloy due to sequential exposure to fatigue,corrosion and fatigue[J].International Journal of Fatigue,1998,20(10):743-748.
[13]	范超华.飞机结构单机寿命监控若干关键问题研究[D].西安:空军工程大学,2010. FAN Chaohua.Study on some critical problem for single aircraft structure life surveillance[D].Xi'an:Air Force Engineering University,2010.(in Chinese)
[14]	张海威,何宇廷,范超华,等.腐蚀/疲劳交替作用下飞机金属材料疲劳寿命计算方法[J].航空学报,2013,34(5):1114-1121. ZHANG Haiwei,HE Yuting,FAN Chaohua,et al.Fatigue life prediction method for aircraft metal material under alternative corrosion/fatigue process[J].Acta Aeronautics et Astronautics Sinica,2013,34(5):1114-1121.(in Chinese)
[15]	Manson S S,Halford G R.Practical implementation of the double linear damage rule and damage curve approach for treating cumulative fatigue damage[J].International Journal of Fracture,1981,17(2):169-192.
[16]	HAN Zhongying,HUANG Xiaoguang,CAO Yuguang,et al.A nonlinear cumulative evolution model for corrosion fatigue damage[J].Journal of Zhejiang University:Science A Applied Physics and Engineering,2014,15(6):447-453.
[17]	Engelhardt G,Strehblow H H.The determination of the shape of developing corrosion pits[J].Corrosion Science,1994,36(10):1711-1725.
[18]	高潮,伍黎明,何宇廷,等.基于能量模型的三维穿透裂纹扩展研究[J].航空动力学报,2015,30(3):639-647. GAO Chao,WU Liming,HE Yuting,et al.Study on three-dimensional through thickness crack growth based on energy model[J].Journal of Aerospace Power,2015,30(3):639-647.(in Chinese)
[19]	Costa J M,Sagués S,Vilarrasa M.Fractal patterns from corrosion pitting[J].Corrosion Science,1991,32(5/6):665-668.