Abstract: In order to study the influence of different aluminum alloy grades and layers on the load-bearing performance of carbon fiber aluminum alloy laminates, this paper taked carbon fiber reinforced aluminum alloy laminates as the research background, and four groups of 3/2 type carbon fiber aluminum alloy specimens composed of two kinds of aluminum alloy materials 2024-T3 and 7075-T6 and two kinds of carbon fiber prepreg layer structure [0/90/0] and [45/0/-45] were taken as research objects, the method of modeling and analysis of ABAQUS software was used. The results show that: The initial stiffness and ultimate load of the four groups of specimens are not different, but there are obvious differences in the ultimate displacements, the ultimate displacements of the specimens with 2024-T3 aluminum alloy are larger than those with 7075-T6 aluminum alloy. The ultimate displacement of specimens with [45/0/-45] layer structure is larger than that with [0/90/0] layer structure. The surface strain of four groups of aluminum alloys is symmetrical distribution, the strain of aluminum alloy with 2024-T3 is obviously larger than that with aluminum alloy 7075-T6, and the strain level of short edge in loading area is obviously higher than that of long edge. There is a clear sequence of damage in the material layer of the specimen, the 0 degree fiber fracture occurs first, the 90 degree fiber second, and the 45 degree fiber finally, 7075-T6 aluminum alloy fracture occurs after fiber fracture, and 2024-T3 aluminum alloy fracture occurs in fiber fracture process. In addition, the finite element analysis is in good agreement with the test, and the ultimate load and the main failure mode are consistent with the test results.

Key words: carbon fiber reinforced aluminum alloy laminate, bearing capacity, ABAQUS, damage