Crack Growth Properties of 7B04 and B95 Superhard Aluminum Alloys
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摘要: 采用根据国内某型飞机飞行特性编制的随机载荷谱，对B95和7B04硬质铝合金进行疲劳试验，获得疲劳裂纹扩展数据和疲劳总寿命，确定裂纹形成寿命，对2种铝合金的疲劳寿命、分散性系数等重要疲劳性能指标进行对比分析。结果表明：7B04铝合金的中值裂纹形成寿命为5 301.9飞行小时，约为B95铝合金的1.55倍，裂纹形成寿命分散系数为1.436 2，远低于B95铝合金的（2.443 9）；7B04铝合金的安全寿命为4 373.82飞行小时，约为B95铝合金的2.2倍，总寿命分散系数为1.502 3，亦远低于B95铝合金的（2.168 9）；7B04铝合金的疲劳裂纹扩展性能明显优于B95铝合金的，可替代B95铝合金制造结构件。Abstract: Fatigue tests were carried out on B95 and 7B04 superhard aluminum alloys under the random load spectrum compiled by the flight characteristics of a domestic aircraft, and the fatigue crack growth data and total fatigue life were obtained. The crack formation life was determined, and the fatigue life, dispersion coefficient and other important fatigue property indexes of the two aluminum alloys were compared and analyzed. The results show that the median crack formation life of 7B04 aluminum alloy was 5 301.9 flight hours, which was about 1.55 times that of B95 aluminum alloy, and the dispersion coefficient of crack formation life was 1.436 2, which was far lower than that of B95 aluminum alloy (2.443 9). The safe life of 7B04 aluminum alloy was 4 373.82 flight hours, which was about 2.2 times that of B95 aluminum alloy, and the total life dispersion coefficient was 1.502 3, which was far lower than that of B95 aluminum alloy (2.168 9). The fatigue crack growth properties of 7B04 aluminum alloy were obviously better than those of B95 aluminum alloy, so it could be used to replace B95 aluminum alloy to manufacture structural members.
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[1] 宁玲. 老龄飞机延寿的一些重要问题[J]. 结构强度研究, 2000(4):53-58. [2] 何宇廷,高潮,张腾,等.飞机结构疲劳/耐久性安全寿命延寿方法[J].空军工程大学学报(自然科学版),2015,16(6):1-6. [3] 魏鹏,何宇廷,舒文军,等.基于威布尔分布的综合分析法在飞机机载产品延寿中的应用[J].航空维修与工程,2010(1):53-55. [4] 黄季墀, 隋福成. 引进先进战斗机延寿取得重大突破的主要技术途径——耐久性修理是重新赋予飞机生命的修理[J]. 飞机设计, 2010, 30(1):1-4. [5] HE Y D, LI C, ZHANG T, et al. Service fatigue life and service calendar life limits of aircraft structure:Aircraft structural life envelope[J]. Aeronautical Journal, 2016, 120(1233):1746-1762.
[6] 石林.取代老龄飞机材料的高强度铝合金[J].航空制造工程,1998(1):15-16. [7] 李秀华.超硬铝合金板材微观组织及性能研究[D].沈阳:沈阳工业大学,2006. [8] 蹇海根,姜锋,郑秀媛,等.航空用高强高韧铝合金疲劳断口特征的研究[J].航空材料学报,2010,30(4):97-102. [9] 李秀华,陈立佳,张凌云.超硬铝合金的微观组织和力学性能的研究[J].沈阳航空工业学院学报,2005, 22(5):15-17. [10] 汝继刚,伊琳娜.7B04铝合金疲劳断裂性能研究[J].轻合金加工技术,2007(10):38-40. [11] 陈群志,韩恩厚,洪海明,等.某型飞机关键结构模拟件疲劳寿命研究[J].机械强度,2004(增刊1):222-225. [12] 张腾.飞机典型结构细节耐久性分析[D]. 西安:空军工程大学, 2012. [13] 高镇同.航空金属材料疲劳性能手册[M].北京:北京航空材料研究所,1981:94-142. [14] 娄路亮, 李付国, 李庆华. 一种计算疲劳裂纹萌生寿命的数值方法[J]. 机械强度, 2000(3):203-205. [15] 何宇廷.飞机结构寿命控制原理与技术[M].北京:国防工业出版社,2017:99-147. [16] 高镇同. 疲劳应用统计学[M]. 北京:国防工业出版社, 1986:199-216.
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