The composite hole circumference of the composite double-bolt joints structure is easy to be damaged due to uneven loading and complex stress state. The penetrate area is usually the weak link of the connection structure. The connecting hole is generally reamed to a standard size circle during aircraft structural maintenance. Thus it is of great significance to study the rules of corresponding distribution and factors of hole influencing after double-pin reaming maintenance. This is of great significance to ensure the airworthiness of structural components and improve the connection performance. This paper took the composite material/aluminum alloy connection structure as the research object， and built a three-dimensional progressive damage analysis model of double-bolt single-shear connection with embedded Hashin failure criterion and improved camanho stiffness reduction coefficient through the ABAQUS software. The experimental verification was carried out， and it was emphatic on the effect of combinations on the tensile static strength and damage in double-nail single-shear connections with different maintenance aperture. The results show that the load-displacement curve and failure mode obtained by the finite element analysis are basically consistent with the test results， with a maximum error of 8.9%.The bolt load of D₂ near the loading end is higher than that of the bolt D₁ near the fixed end of the metal plate. The D₂ diameter increased（W/D₂ decrease） with the standard connection parameters can improve the stress concentration at the edge of the double-bolted connection hole， and increase the initial and ultimate strength. But excessive D₂ diameter will reduce the net cross-sectional area of the composite sheet， resulting in a decrease in joint strength.The increase of the friction coefficient will prolong the occurrence of the initial damage of the composite plate， resulting in a significant delay in the attenuation of stiffness.