Study on Corrosion and Fatigue Alternation of Aerospace Aluminum Alloy Welded Joints by Variable Polarity Plasma Arc Welding
GAO Chong1,2, DONG Lihong2,*, WANG Haidou3,*, LI Bin2, LYU Xiaoren1, NIE Jiapeng2
1 School of Mechanical Engineering, Shenyang University of Technology, Shenyang 110870, China 2 National Key Lab for Remanufacturing, Army Academy of Armored Forces, Beijing 100072, China 3 National Engineering Research Center for Remanufacturing, Army Academy of Armored Forces, Beijing 100072, China
Abstract: With the concept of reusable spacecraft, multiple air-to-air round trips and ground repair processes have made alternating problems of corrosion and fatigue on reusable spacecraft cannot be ignored. In this work, variable polarity plasma arc welding was used to join 5 mm thick 5A06 aluminum magnesium alloy. The alternating corrosion-fatigue test was carried out to study the effect of different unit corrosion time on fatigue life. The specimens were characterized by scanning electron microscope and laser confocal microscope. The damage characteristics after the alternate action of corrosion and fatigue were analyzed. The results show that with the increase of unit corrosion time, the average alternating corrosion-fatigue life decrease first and then tend to be stable. That is mainly due to the fact that the corrosion passivated the fatigue crack tip and form new pitting pits. At the same time, the intrusion/extrusion and microcracks during the fatigue process reduce the surface stress concentration and increase the fatigue life relatively, thus the stable state of life reflects. The fracture locations are all in the heat affected zone, which mainly because the welding heat affected zone has poor corrosion resistance and easy to form serious corrosion damage. The large corrosion pits cause serious stress concentration and accelerates crack initiation.
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2024, Vol. 38 
