含边缘裂纹铝合金厚板的复合材料双面修补研究  

Double-Side Bonded Composite Repairs of Edge-Cracked Thick Aluminum Alloy Plates

作　　者：贺旺 孙运刚 杜永华 古兴瑾[2] HE Wang;SUN Yungang;DU Yonghua;GU Xingjin(State Owned Wuhu Machinery Works,Wuhu,241007,China;College of Aerospace Engineering,Nanjing University of Aeronautics&Astronautics,Nanjing,210016,China)

机构地区：[1]国营芜湖机械厂,芜湖241007 [2]南京航空航天大学航空学院,南京210016

出　　处：《南京航空航天大学学报》2019年第4期547-552,共6页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：采用表面打磨,80℃、接触压固化的方法,利用碳纤维/双马复合材料预固化补片对边缘裂纹的铝合金厚板进行双面胶接修补,测试修补前后的静态和疲劳性能,并结合高低温老化和常温油浸试验考核其耐煤油性。结果表明:修补后平均破坏载荷由94.313 kN增加到143.593 kN,提高了52.25%;疲劳寿命由2 019次循环增加到34 698次循环,提高了16.19倍;临界裂纹长度由13.5 mm增加为27.5 mm;裂纹扩展速率由2.72 mm/1 000循环降低为0.59 mm/1 000循环。在300次循环高低温油浸及180 d的常温油浸试验条件下,燃油对试验件疲劳性能无影响,同时修补试验件对煤油品质无明显影响。Using the method of surface grinding,temperature of 80℃,and contact pressure curing,double?side adhesive repair of edge?cracked thick aluminum alloy plates is conducted by carbon fiber/bismaleimides composite materials.Performance of static and fatigue before and after repair is tested,and its kerosene resistance is examined by aging of high and low temperatures and normal temperature oil immersion test.The results show that the average damage load after repair increases from 94.313 kN to 143.593 kN,an increase of 52.25%;the fatigue life increases from 2 019 cycles to 34 698 cycles,an increase of 16.19 times;the critical crack length increases from 13.5 mm to 27.5 mm;the crack growth rate reduces from 2.72 mm/1 000 cycles to 0.59 mm/1 000 cycles.Under the oil immersion 300 cycles of high and low temperatures and 180 d of normal temperature oil immersion tests,the fuel has no effect on the fatigue performance of the test piece,and the repaired test pieces have no significant effect on the kerosene quality.

关 键 词：铝合金厚板 复合材料 破坏载荷 疲劳寿命 耐煤油性 

分 类 号：V257[一般工业技术—材料科学与工程]