Effect of stacking sequence on fatigue behavior of CFRP⁃Al joint

被引：0
|
作者：
Zou T. [1 ]
Ju Y. [1 ]
Guan Y. [1 ]
Li Z. [1 ]
Chen H. [1 ]
机构：
[1] College of Safety Science and Engineering, Civil Aviation University of China, Tianjin
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2023年 / 44卷 / 18期
关键词：
CFRP-Al; crack propagation; finite element simulation; stacking sequence; stiffness degradation; stress distribution;
D O I：
10.7527/S1000-6893.2023.28264
中图分类号：
学科分类号：
摘要：
The finite element simulation model of Carbon Fiber Reinforced Plastics（CFRP）-aluminum single lap adhesive joint was established by Abaqus. The stacking sequences of CFRP laminate were set as［0/90］4s，［0/45/ −45/90］2s and［45/−45］4s. And the Cyclic Cohesive Zone Model（CCZM）was used to simulate the damage and evolution of the adhesive layer. The stiffness degradation，crack propagation and stress distribution of the joint were analyzed to investigate the effect of stacking sequence on the joint fatigue behavior. The experimental values of the joint fatigue life were compared with the simulated values to verify the validity of the model. The results show that from［0/90］4s to［0/45/− 45/90］2s，then to［45/− 45］4s，as the proportion of ±45° plies in CFRP laminates increases，the proportion of the joint damage accumulation stage to the total fatigue life gradually decreases and the proportion of the fatigue crack extension stage gradually increases. In addition，the joint stress mainly propagates through the fiber from the CFRP end to the aluminum end，and the stress concentration area is prone to occur at the intersection of ±45° plies，which destroys the uniformity of crack propagation rate，leading to the gradual increase in the crack growth rate difference between the middle region and the two sides of the joint with the increase of ±45° plies，and eventually the radian of the adhesive layer failure increases. © 2023 AAAS Press of Chinese Society of Aeronautics and Astronautics. All rights reserved.
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