2E12-T3铝合金蒙皮环向对接结构的疲劳性能  

Fatigue Performance of 2E12-T3 Aluminum Alloy Skin Circumferential Docking Structure

作　　者：彭航 秦剑波 张彦军 PENG Hang;QIN Jianbo;ZHANG Yanjun(The First Aircraft Design and Research Institute of AVIC,Xi'an 710089,China)

机构地区：[1]航空工业第一飞机设计研究院,西安710089

出　　处：《机械工程材料》2021年第10期29-33,42,共6页Materials For Mechanical Engineering

摘　　要：通过有限元仿真确定蒙皮环向对接结构的疲劳危险部位,计算得到2024-T3铝合金对接结构的理论细节疲劳额定值(DFR)。对2E12-T3铝合金蒙皮环向对接结构进行疲劳试验,分析了疲劳断裂位置和断口形貌,计算得到该对接结构的试验DFR,并与2024-T3铝合金对接结构的理论DFR进行对比分析。结果表明:蒙皮环向对接结构试样均在蒙皮端部钉孔处发生疲劳破坏,与有限元分析得到的结构薄弱部位一致;裂纹起源于蒙皮与带板贴合面且与加载方向垂直的蒙皮孔壁上,裂纹扩展区存在疲劳条带和少数韧窝,瞬断区存在韧窝及空洞;2E12-T3铝合金对接结构的DFR相比于2024-T3铝合金对接结构提升约13.9%。The fatigue dangerous location of the skin circumferential docking structure was determined by finite element simulation.The theoretical detailed fatigue rating(DFR)of the 2024-T3 aluminum alloy docking structure was calculated.Fatigue tests were conducted on the 2 E12-T3 aluminum alloy skin circumferential docking structure,and the fatigue fracture location and fracture morphology were analyzed.The test DFR of the docking structure was calculated,and compared with the theoretical DFR of the 2024-T3 aluminum alloy docking structure.The results show that the fatigue failure occurred at nail holes at the end of the skin circumferential docking structure samples,which was consistent with the structure weak location determined by the finite element analysis.The cracks initiated at the skin hole wall perpendicular to the loading direction at the skin and the strip joint surface.Fatigue bands and a few dimples existed in the crack propagation zone,and dimples and cavities in the instantaneous zone.The DFR of the 2E12-T3 aluminum alloy docking structure was about 13.9% higher than that of 2024-T3 aluminum alloy docking structure.

关 键 词：有限元 细节疲劳额定值(DFR) 断口分析 疲劳寿命 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]