基于腐蚀电流的加速腐蚀关系可靠性模型
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摘要
目的通过对加速腐蚀关系的研究,为飞机的日历寿命的确定提供依据。方法首先提出基于腐蚀电流的加速腐蚀关系可靠性模型,并通过测试极化曲线的方法得到LY12和ZL115两种飞机常用铝合金材料在蒸馏水及不同浓度Na Cl溶液中的腐蚀电流。结果由于材料缺陷分布的随机性,铝合金的腐蚀电流具有随机特征,且随着盐浓度的增加而增大。两种铝合金材料的加速腐蚀关系系数在统计上存在较大的差异,在3.5%盐浓度下(温度)考虑95%置信度的加速腐蚀关系系数,LY12铝合金为3.53、ZL115为2.32。结论本文基于腐蚀电流的加速腐蚀关系的研究可以很好地为飞机日历寿命确定提供依据。
Objective To provide a basis for determining the calendar life of aircraft through studying the relationship of accelerated corrosion. Methods The reliability model of accelerated corrosion relationship based on corrosion current was proposed. The corrosion current of LY12 and ZL115 aluminum alloy materials in distilled water and NaCl solution with different concentration were obtained by means of polarization curve test. Results The corrosion current of random aluminum alloy with defect distribution was random and increased with the increase of salt. The accelerated corrosion relationship coefficient of the two kinds of aluminum alloy materials was statistically different. Accelerated corrosion relationship coefficient of LY12 aluminum alloy with 95% confidence under 3.5% salt concentration(temperature) was 3.53, ZL115=2.32 respectively. Conclusion The study of accelerated corrosion relationship based on corrosion current in this paper can provide a basis for determining the calendar life of aircraft.
Objective To provide a basis for determining the calendar life of aircraft through studying the relationship of accelerated corrosion. Methods The reliability model of accelerated corrosion relationship based on corrosion current was proposed. The corrosion current of LY12 and ZL115 aluminum alloy materials in distilled water and NaCl solution with different concentration were obtained by means of polarization curve test. Results The corrosion current of random aluminum alloy with defect distribution was random and increased with the increase of salt. The accelerated corrosion relationship coefficient of the two kinds of aluminum alloy materials was statistically different. Accelerated corrosion relationship coefficient of LY12 aluminum alloy with 95% confidence under 3.5% salt concentration(temperature) was 3.53, ZL115=2.32 respectively. Conclusion The study of accelerated corrosion relationship based on corrosion current in this paper can provide a basis for determining the calendar life of aircraft.
引文
[1]张福泽.飞机日历翻修期与总日历寿命确定方法和预计公式[J].航空学报,2005,26(4):458-460.
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[3]PAN S,SANKARAN M.Damage Tolerance Approach for Probabilistic Pitting Corrosion Fatigue Life Prediction[J].Engineering Fracture Mechanics,2001,68(13):1493-1507
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[5]CLAUDIA F,DIETMAR E.Corrosion,Fatigue and Corrosion Fatigue Behaviour of Metal Implant Materials,Especially Titanium alloys[J].International Journal of Fatigue,2010,32(6):929-935.
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[11]张福泽,叶序彬,宋钧,等.飞机日历寿命试验的介质成分确定和加速方法[J].航空学报,2008,29(4):873-879.
[12]陈群志,李喜明,周希沅,等.飞机结构典型环境腐蚀当量关系研究[J].航空学报,1998,19(4):414-418.
[13]刘文珽,李玉海,陈群志,等.飞机结构腐蚀部位涂层加速试验环境谱研究[J].北京航空航天大学学报,2002,28(1):109-112.
[14]曹定国,任三元,王浩伟.环境严酷性指数腐蚀当量方法及其应用研究[J].航空学报,2008,29(3):634-639.
[15]张栋.确定飞机日历寿命用的当量环境谱研究[J].航空学报,2000,21(2):128-133.
[16]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.
[2]LI J,LI M,SUN Z.Development of an Artificial Climatic Complex Accelerated Corrosion Tester and Investigation of Complex Accelerated Corrosion Test Methods[J].Corrosion,1999,55(5):498-501.
[3]PAN S,SANKARAN M.Damage Tolerance Approach for Probabilistic Pitting Corrosion Fatigue Life Prediction[J].Engineering Fracture Mechanics,2001,68(13):1493-1507
[4]MARGERY E.HOFFMAN,PAUL C.Hoffman,Corrosion and Fatigue Research-Structural Issues and Relevance to Naval Aviation[J].International Journal of Fatigue,2001,23(S1):1-10.
[5]CLAUDIA F,DIETMAR E.Corrosion,Fatigue and Corrosion Fatigue Behaviour of Metal Implant Materials,Especially Titanium alloys[J].International Journal of Fatigue,2010,32(6):929-935.
[6]张丹峰,谭晓明,戚佳睿.飞机结构件腐蚀监测研究[J].环境技术,2017,35(4):32-34.
[7]杨晓华,姚卫星,陈跃良.加速疲劳寿命试验在飞机结构日历寿命研究中的应用[J].腐蚀科学与防护技术,2002,14(3):172-174.
[8]周希沅.飞机结构的当量环境谱与加速试验谱[J].航空学报,1996,17(5):613-616.
[9]周希沅.中国飞机结构腐蚀分区和当量环境谱[J].航空学报,1999,20(3):230-233.
[10]杨晓华,金平.飞机使用环境谱的编制[J].装备环境工程,2010,7(6):99-102.
[11]张福泽,叶序彬,宋钧,等.飞机日历寿命试验的介质成分确定和加速方法[J].航空学报,2008,29(4):873-879.
[12]陈群志,李喜明,周希沅,等.飞机结构典型环境腐蚀当量关系研究[J].航空学报,1998,19(4):414-418.
[13]刘文珽,李玉海,陈群志,等.飞机结构腐蚀部位涂层加速试验环境谱研究[J].北京航空航天大学学报,2002,28(1):109-112.
[14]曹定国,任三元,王浩伟.环境严酷性指数腐蚀当量方法及其应用研究[J].航空学报,2008,29(3):634-639.
[15]张栋.确定飞机日历寿命用的当量环境谱研究[J].航空学报,2000,21(2):128-133.
[16]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.