多种服役环境下航空铝合金疲劳裂纹扩展行为
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摘要
通过收集机场环境数据并依据环境谱编谱流程,编制出试验室环境下航空铝合金加速腐蚀试验谱,并依据该谱开展LD2CS铝合金预腐蚀疲劳试验。统计分析试验数据,利用影响平均值方法,筛选出三个重要腐蚀损伤表征量,即最大蚀坑深度、最大蚀坑宽度、点蚀率。通过归一化无量纲处理和加权平均方法,计算出腐蚀损伤综合指标α。对比不同损伤程度下预制裂纹疲劳扩展行为特点,定义腐蚀加速系数Ω(α)。利用加速腐蚀第18—20a的试验数据验证Ω(α)表达式的有效性,得到预测值相对误差均小于10%,这说明修正后的疲劳裂纹扩展公式适用于表示腐蚀损伤对长裂纹扩展的加速作用,为航空铝合金的损伤容限设计提供新的思路。
The aviation aluminum alloy accelerated corrosion test spectrum was established according to the environment spectrum conducting process after collecting the airports environment data. Based on the accelerated corrosion test spectrum,aluminum alloy LD2 CS pre-corroded fatigue test was carried out. Test data were analyzed statistically and the three main corrosion damage characterization factors,namely maximum pit depth,maximum pit width and pit surface rate,were sifted out by using MIV( mean impact value) method. Then the corrosion damage composite indictorα was computed by applying the normalization non-dimension and the weighted average methods. By comparing the characteristics of fatigue precrack propagation behaviors at different corrosion damage levels,the corrosion acceleration coefficient Ω( α) was defined to correct the classical fatigue crack growth formula. The validity of Ω( α) expression was verified by employing test data corroding the 18 th to 20 th equivelent years and the relative errors were all below 10%. It demonstrates that the corrected fatigue crack growth function in flight transfer environment is appropriate for reflecting the corrosion damage acceleration effect on crack propagation,which proposing new ideas for aviation aluminum alloy damage tolerance design.
The aviation aluminum alloy accelerated corrosion test spectrum was established according to the environment spectrum conducting process after collecting the airports environment data. Based on the accelerated corrosion test spectrum,aluminum alloy LD2 CS pre-corroded fatigue test was carried out. Test data were analyzed statistically and the three main corrosion damage characterization factors,namely maximum pit depth,maximum pit width and pit surface rate,were sifted out by using MIV( mean impact value) method. Then the corrosion damage composite indictorα was computed by applying the normalization non-dimension and the weighted average methods. By comparing the characteristics of fatigue precrack propagation behaviors at different corrosion damage levels,the corrosion acceleration coefficient Ω( α) was defined to correct the classical fatigue crack growth formula. The validity of Ω( α) expression was verified by employing test data corroding the 18 th to 20 th equivelent years and the relative errors were all below 10%. It demonstrates that the corrected fatigue crack growth function in flight transfer environment is appropriate for reflecting the corrosion damage acceleration effect on crack propagation,which proposing new ideas for aviation aluminum alloy damage tolerance design.
引文
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[16]吴洪丽,蒋永辉.软件可靠性影响因素权重分析[J].计算机工程与应用,2010,46(33):58-62.WU Hongli, JIANG Yonghui. Weight analysis of factors affecting software reliability[J]. Computer Engineering and Applications,2010,46(33):58-62.(in Chinese)
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[19]李旭东,孔光明,穆志韬.穿透型疲劳裂纹扩展与铝合金局部点蚀损伤特征参数的依存性分析[J].腐蚀与防护,2015,36(11):1049-1052,1057.LI Xudong, KONG Guangming, MU Zhitao. Dependent analysis of through out crack propagation on localized pitting corrosion parameters of aluminum alloy[J]. Corrosion&Protection,2015, 36(11):1049-1052, 1057.(in Chinese)
[20]Biallas G,Essert M,Maier H J. Influence of environment on fatigue mechanisms in high-temperature titanium alloy IMI834[J]. International Journal of Fatigue, 2005,27(10/11/12):1485-1493.
[21]Jones K,Shinde S R,Clark P N,et al. Effect of prior corrosion on short crack behavior in 2024-T3 aluminum alloy[J]. Corrosion Science,2008,50(9):2588-2595.
[22]Andersson H,Persson C. In-situ SEM study of fatigue crack growth behavior in IN718[J]. International Journal of Fatigue,2004,26(3):211-219.
[23]徐富强,刘相国.基于优化的RBF神经网络的变量筛选方法[J].计算机系统应用,2012,21(3):206-208.XU Fuqiang, LIU Xiangguo. Variables screening methods based on the optimization of RBF neural network[J].Computer Systems&Applications,2012,21(3):206-208.(in Chinese)
[24]董登科,王俊扬.关于军用飞机服役日历年限评定用的当量环境谱[J].航空学报,1998,19(4):451-455.DONG Dengke, WANG Junyang. Equivelent environment spectrum research on service calendar time for fighter aircraft[J]. Acta Aeronautica et Astronautica Sinica,1998,19(4):451-455.(in Chinese)
[25]穆志韬,柳文林,于战樵.飞机服役环境当量加速腐蚀折算方法研究[J].海军航空工程学院学报,2007,22(3):301-304.MU Zhitao,LIU Wenlin,YU Zhanqiao. Research on accelerated corrosion equivalent conversion method of aircraft service environment[J]. Journal of Naval Aeronautical Engineering Institute, 2007, 22(3):301-304.(in Chinese)
[26]陈群志,孙祚东,韩恩厚,等.典型飞机结构加速腐蚀试验方法研究[J].装备环境工程,2004,1(5):13-17.CHEN Qunzhi,SUN Zuodong,HAN Enhou,et al. Study on accelerated corrosion test methods of typical aircraft structure[J]. Equipment Environmental Engineering,2004,1(5):13-17.(in Chinese)
[27]宋恩鹏,刘文珽,杨旭.飞机内部腐蚀关键部位加速试验环境谱研究[J].航空学报,2006,27(4):646-649.SONG Enpeng, LIU Wenting, YANG Xu. Study on accelerated corrosion test environment spectrum for internal aircraft structure[J]. Acta Aeronautica et Astronautica Sinica,2006,27(4):646-649.(in Chinese)
[28]任和,冯元生,王琛.运七机翼腐蚀失效模型及其可靠性分析[J].腐蚀科学与防护技术,1998,10(4):212-216.REN He,FENG Yuansheng,WANG Chen. The corrosion failure distribution and reliability of Y-7 aircraft wing[J].Corrosion Science and Protection Technology,1998,10(4):212-216.(in Chinese)
[2]Gruenberg K M,Craig B A,Hillberry B M,et al. Predicting fatigue life of pre-corroded 2024-T3 aluminum[J].International Journal of Fatigue,2004,26(7):629-640.
[3]Arunachalam S,Fawaz S. Test method for corrosion pit-tofatigue crack transition from a corner of hole in 7075-T651aluminum alloy[J]. International Journal of Fatigue,2016,91(5):50-58.
[4]Rokhlin S I,Kim J Y,Nagy H,et al. Effect of pitting corrosion on fatigue crack initiation and fatigue life[J].Engineering Fracture Mechanics,1999,62(4/5):425-444.
[5]张有宏,吕国志,任克亮,等.不同环境下LY12CZ铝合金表面腐蚀损伤演化规律研究[J].航空学报,2007,28(1):142-145.ZHANG Youhong,LYU Guozhi,REN Keliang,et al. The evolution rhythm of surface corrosion damage of LY12-CZ aluminum in varied environments[J]. Acta Aeronautica et Astronautica Sinica,2007,28(1):142-145.(in Chinese)
[6]Sankaran K K,Perez R,Jata K V. Effects of pitting corrosion on the fatigue behavior of aluminum alloy 7075-T6:modeling and experimental studies[J]. Materials Science and Engineering A,2001,297(1/2):223-229.
[7]Crawford B R,Loader C,Liu Q C,et al. Can pitting corrosion change the location of fatigue failures in aircraft?[J].International Journal of Fatigue,2014,61:304-314.
[8]Weber M,Eason P D,zde爧H,et al. The effect of surface corrosion damage on the fatigue life of 6061-T6 aluminum alloy extrusions[J]. Materials Science and Engineering A,2017,690:427-432.
[9]Zhou X Z,Zheng J J. A numerical method for predicting the time to surface cracking of corrosion affected RC structures[J]. Fracture and Damage Mechanics V,2006,11:55-58.
[10]贺小帆,刘文珽,向锦武. C-T曲线通用性分析和试验研究[J].航空学报,2005,26(2):184-189.HE Xiaofan,LIU Wenting,XIANG Jinwu. Analysis and test of generality of C-T curve[J]. Acta Aeronautica et Astronautica Sinica,2005,26(2):184-189.(in Chinese)
[11]张蕾,陈群志,宋恩鹏,等.某型飞机典型疲劳关键件加速腐蚀条件下C-T曲线的测定[J].机械强度,2004,26(z1):55-57.ZHANG Lei,CHEN Qunzhi,SONG Enpeng,et al. C-T curve of the critical part of aircraft structure under corrosion condition[J]. Journal of Mechanical Strength, 2004,26(z1):55-57.(in Chinese)
[12]刘学君,杨晓华,辛志东,等.某型飞机典型结构危险部位地面停放预腐蚀影响系数曲线的试验测定[J].装备环境工程,2014(6):79-83.LIU Xuejun,YANG Xiaohua,XIN Zhidong,et al. C-T curve experimental determination of critical parts of an aircraft typical structure[J]. Equipment Environmental Engineering,2014(6):79-83.(in Chinese)
[13]蔡剑,刘道新,叶作彦,等.腐蚀与交变载荷循环作用对2A12-T4铝合金疲劳寿命的影响[J].中国腐蚀与防护学报,2015,35(1):61-68.CAI Jian,LIU Daoxin,YE Zuoyan,et al. Influence of cyclic action of corrosion and alternate load on fatigue life of 2A12-T4 aluminum alloy[J]. Journal of Chinese Society for Corrosion and Protection,2015,35(1):61-68.(in Chinese)
[14]马少华,回丽,周松,等.腐蚀环境对预腐蚀铝合金腐蚀疲劳性能的影响[J].材料工程,2015,43(2):91-95.MA Shaohua, HUI Li, ZHOU Song, et al. Influence of corrosion environments on corrosion fatigue property of precorroded aluminum alloy[J]. Journal of Materials Engineering,2015,43(2):91-95.(in Chinese)
[15]王池权,熊峻江,马少俊,等.航空铝合金材料腐蚀裂纹扩展性能试验[J].北京航空航天大学学报,2017,43(5):935-941.WANG Chiquan,XIONG Junjiang,MA Shaojun,et al. Tests for corrosion crack propagation behavior of aeronautical aluminum alloys[J]. Journal of Beijing University of Aeronautics and Astronautics,2017,43(5):935-941.(in Chinese)
[16]吴洪丽,蒋永辉.软件可靠性影响因素权重分析[J].计算机工程与应用,2010,46(33):58-62.WU Hongli, JIANG Yonghui. Weight analysis of factors affecting software reliability[J]. Computer Engineering and Applications,2010,46(33):58-62.(in Chinese)
[17]Li X D,Wang X S,Ren H H,et al. Effect of prior corrosion state on the fatigue small cracking behavior of 6151-T6aluminum alloy[J]. Corrosion Science,2012,55:26-33.
[18]Kand J,Fu R D,Luan G H,et al. In-situ investigation on the pitting corrosion behavior of friction stir welder joint of AA2024-T3 aluminum alloy[J]. Corrosion Science,2010,52(2):620-626.
[19]李旭东,孔光明,穆志韬.穿透型疲劳裂纹扩展与铝合金局部点蚀损伤特征参数的依存性分析[J].腐蚀与防护,2015,36(11):1049-1052,1057.LI Xudong, KONG Guangming, MU Zhitao. Dependent analysis of through out crack propagation on localized pitting corrosion parameters of aluminum alloy[J]. Corrosion&Protection,2015, 36(11):1049-1052, 1057.(in Chinese)
[20]Biallas G,Essert M,Maier H J. Influence of environment on fatigue mechanisms in high-temperature titanium alloy IMI834[J]. International Journal of Fatigue, 2005,27(10/11/12):1485-1493.
[21]Jones K,Shinde S R,Clark P N,et al. Effect of prior corrosion on short crack behavior in 2024-T3 aluminum alloy[J]. Corrosion Science,2008,50(9):2588-2595.
[22]Andersson H,Persson C. In-situ SEM study of fatigue crack growth behavior in IN718[J]. International Journal of Fatigue,2004,26(3):211-219.
[23]徐富强,刘相国.基于优化的RBF神经网络的变量筛选方法[J].计算机系统应用,2012,21(3):206-208.XU Fuqiang, LIU Xiangguo. Variables screening methods based on the optimization of RBF neural network[J].Computer Systems&Applications,2012,21(3):206-208.(in Chinese)
[24]董登科,王俊扬.关于军用飞机服役日历年限评定用的当量环境谱[J].航空学报,1998,19(4):451-455.DONG Dengke, WANG Junyang. Equivelent environment spectrum research on service calendar time for fighter aircraft[J]. Acta Aeronautica et Astronautica Sinica,1998,19(4):451-455.(in Chinese)
[25]穆志韬,柳文林,于战樵.飞机服役环境当量加速腐蚀折算方法研究[J].海军航空工程学院学报,2007,22(3):301-304.MU Zhitao,LIU Wenlin,YU Zhanqiao. Research on accelerated corrosion equivalent conversion method of aircraft service environment[J]. Journal of Naval Aeronautical Engineering Institute, 2007, 22(3):301-304.(in Chinese)
[26]陈群志,孙祚东,韩恩厚,等.典型飞机结构加速腐蚀试验方法研究[J].装备环境工程,2004,1(5):13-17.CHEN Qunzhi,SUN Zuodong,HAN Enhou,et al. Study on accelerated corrosion test methods of typical aircraft structure[J]. Equipment Environmental Engineering,2004,1(5):13-17.(in Chinese)
[27]宋恩鹏,刘文珽,杨旭.飞机内部腐蚀关键部位加速试验环境谱研究[J].航空学报,2006,27(4):646-649.SONG Enpeng, LIU Wenting, YANG Xu. Study on accelerated corrosion test environment spectrum for internal aircraft structure[J]. Acta Aeronautica et Astronautica Sinica,2006,27(4):646-649.(in Chinese)
[28]任和,冯元生,王琛.运七机翼腐蚀失效模型及其可靠性分析[J].腐蚀科学与防护技术,1998,10(4):212-216.REN He,FENG Yuansheng,WANG Chen. The corrosion failure distribution and reliability of Y-7 aircraft wing[J].Corrosion Science and Protection Technology,1998,10(4):212-216.(in Chinese)
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