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材料导报  2024, Vol. 38 Issue (6): 22020135-6    https://doi.org/10.11896/cldb.22020135
  金属与金属基复合材料 |
基于VARI工艺的碳纤维复合材料快速修理飞机铝合金裂纹的研究
汪愿1,2,*, 孙运刚1,2, 符彬1, 刘文浩1,2, 宣善勇1,2, 刘鹏1
1 国营芜湖机械厂,安徽 芜湖 241007
2 安徽省航空复合材料维修工程技术研究中心,安徽 芜湖 241007
Research on Rapid Repair of Aircraft Aluminum Alloy Cracks with Carbon Fiber Composites Based on VARI Process
WANG Yuan1,2,*, SUN Yungang1,2, FU Bin1, LIU Wenhao1,2, XUAN Shanyong1,2, LIU Peng1
1 State-operated Machinery Factory of Wuhu, Wuhu 241007, Anhui, China
2 Anhui Aeronautical Composite Maintenance Engineering Technology Research Center, Wuhu 241007, Anhui, China
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摘要 考虑到飞机战伤抢修需求,在现有的复合材料胶接修理基础上提出了一种基于真空辅助树脂灌注(VARI)工艺的金属裂纹快速修理方法,通过静力拉伸和疲劳实验将VARI修理工艺与传统湿法胶接修理工艺、机械补强修理工艺进行对比,获得了不同修理工艺下实验件的静强度恢复率、疲劳寿命、修理时间及比静拉伸强度恢复率,借助有限元分析法深入研究了VARI修理件的损伤过程,并以比静拉伸强度恢复率为指标,利用Design Expert软件进一步优化了修理补片参数。结果表明:在三种修理工艺中,VARI修理工艺效果最佳,采用VARI修理的实验件静强度能恢复至完好实验件的90.3%,疲劳寿命相比未修理实验件增长了31.4倍;与传统湿法胶接修理相比,采用VARI修理可将修理时间缩短60.2%;与机械补强修理相比,采用VARI修理可将实验件增重降低53.5%,比静拉伸强度恢复率提高146.6%;对于长度为20 mm的裂纹,补片长度60 mm、宽度64.8 mm、铺层数目四层(即补片厚度1 mm)为最优补片参数。
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汪愿
孙运刚
符彬
刘文浩
宣善勇
刘鹏
关键词:  飞机铝合金裂纹  真空辅助树脂灌注修理  疲劳寿命  比静拉伸强度恢复率  有限元模拟    
Abstract: Considering the needs of aircraft battle damage repair, based on the bonded composite repairs, a metal crackrapid repair method based on vacuum assisted resin infusion (VARI) process was studied. The VARI repair process was compared with the traditional wet bonded repair process and mechanical reinforcement repair process through static tension and fatigue experiments, the static strength recovery rate, fatigue life, repair time and specific static strength recovery rate of the specimens under different repair processes were obtained. The damage process of the VARI repair specimen was deeply studied with the help of finite element analysis method. Taking the specific static tensile strength recovery rate as the index, the repair patch parameters were further optimized by using Design Expert software. The results show that among the three repair processes, the quality of VARI repair process is the best. The static strength of the specimen repaired by VARI can be restored to 90.3% of the intact specimen, and the fatigue life is 31.4 times longer than that of the non repaired specimen; compared with the traditional wet bonding repair, the repair time can be shortened by 60.2% by using VARI repair; compared with mechanical strengthening repair, VARI repair can reduce the increase of specimen weight by 53.5% and increase the specific static strength recovery rate by 146.6%; for the crack with a length of 20 mm, the patch length of 60 mm, the width of 64.8 mm and the number of patch layers of 4 (the patch thickness of 1 mm) are the optimal patch parameters.
Key words:  aircraft aluminum alloy cracks    vacuum assisted resin infusion repair    fatigue life    specific static tensile strength recovery rate    finite element simulation
出版日期:  2024-03-25      发布日期:  2024-04-07
ZTFLH:  TB332  
基金资助: 安徽省科技重大专项(202203a05020039)
通讯作者:  *汪愿,2020年4月毕业于南京航空航天大学,获得材料工程专业硕士学位,发表一篇SCI论文。现任职于国营芜湖机械厂,主要研究方向为航空装备复合材料修理设计。   
引用本文:    
汪愿, 孙运刚, 符彬, 刘文浩, 宣善勇, 刘鹏. 基于VARI工艺的碳纤维复合材料快速修理飞机铝合金裂纹的研究[J]. 材料导报, 2024, 38(6): 22020135-6.
WANG Yuan, SUN Yungang, FU Bin, LIU Wenhao, XUAN Shanyong, LIU Peng. Research on Rapid Repair of Aircraft Aluminum Alloy Cracks with Carbon Fiber Composites Based on VARI Process. Materials Reports, 2024, 38(6): 22020135-6.
链接本文:  
https://www.mater-rep.com/CN/10.11896/cldb.22020135  或          https://www.mater-rep.com/CN/Y2024/V38/I6/22020135
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