TY - GEN
T1 - Fatigue life prediction of aluminum-lithium alloy considering impact effects
AU - Li, Lei
AU - Shi, Qiangbin
AU - Wang, Xuan
N1 - Publisher Copyright:
© 2023 SPIE.
PY - 2023
Y1 - 2023
N2 - The C919 aircraft reflects the combination of maturity and advanced in the selection of structural materials, and adopts a large number of third-generation aluminum-lithium alloy materials marked by 2060, which has the advantages of high specific stiffness and high specific strength. During aircraft operation, low-energy impactors such as hail and gravel can hit the surface of the aircraft, forming minor pit defects at the skin and forming local stress concentrations, thereby significantly reducing the fatigue life of the aircraft structure. In this paper, the 2mm thick 2060 aluminum-lithium alloy skin is used as the research object, the impact test is carried out first, and the fatigue test is carried out after the impact is completed, and the finite element model is established in the ABAQUS software to simulate the impact, and the nominal stress and stress concentration factor of the dangerous part are clarified, and the fatigue life prediction is carried out by the nominal stress method, and compared with the fatigue test results, the results show that the life prediction by the nominal stress method can provide a reference for the regular maintenance of the aircraft.
AB - The C919 aircraft reflects the combination of maturity and advanced in the selection of structural materials, and adopts a large number of third-generation aluminum-lithium alloy materials marked by 2060, which has the advantages of high specific stiffness and high specific strength. During aircraft operation, low-energy impactors such as hail and gravel can hit the surface of the aircraft, forming minor pit defects at the skin and forming local stress concentrations, thereby significantly reducing the fatigue life of the aircraft structure. In this paper, the 2mm thick 2060 aluminum-lithium alloy skin is used as the research object, the impact test is carried out first, and the fatigue test is carried out after the impact is completed, and the finite element model is established in the ABAQUS software to simulate the impact, and the nominal stress and stress concentration factor of the dangerous part are clarified, and the fatigue life prediction is carried out by the nominal stress method, and compared with the fatigue test results, the results show that the life prediction by the nominal stress method can provide a reference for the regular maintenance of the aircraft.
KW - Aluminum-lithium alloy
KW - Fatigue life
KW - Impact
KW - Nominal stress method
KW - Stress concentration factor
UR - http://www.scopus.com/inward/record.url?scp=85176125363&partnerID=8YFLogxK
U2 - 10.1117/12.3007210
DO - 10.1117/12.3007210
M3 - 会议稿件
AN - SCOPUS:85176125363
T3 - Proceedings of SPIE - The International Society for Optical Engineering
BT - Ninth International Conference on Mechanical Engineering, Materials, and Automation Technology, MMEAT 2023
A2 - Dong, Huajun
A2 - Yu, Hailiang
PB - SPIE
T2 - 9th International Conference on Mechanical Engineering, Materials, and Automation Technology, MMEAT 2023
Y2 - 9 June 2023 through 11 June 2023
ER -