Abstract: In the design of the filament wound case of the solid rocket motor, the connection between the shell and the skirt is mainly achieved through adhesive technology, which is very important for ensuring the effectiveness of the load transfer. However, the performance of the solid rocket motor may be directly compromised if there exhibits a weak adhesion or disadhesion on the bonding interface. In order to solve this problem, the bonding performance between the filament wound case and the skirt of solid rocket motor was studied deeply in this paper. According to the standards of the aerospace industry, the mechanical performance parameters of the adhesive used in the paper were determined through shear performance tests of the adhesive specimen. On this basis, the cohesive force model was used to simulate the behavior of the progressive failure of the bonding during the process of loading. Compared with the test results, the error was less than 3%, which verified the validity of the numerical simulation. The bonding performance between the shell and the skirt with a diameter of 400 mm was analyzed. The strain results of the outermost shell were extracted and compared with the test results. The trend of the test and the numerical simulation results was consistent, and the error was less than 7%, which verified the effectiveness of the numerical simulation once again. Further investigations have been carried out on the effects of the bonding performance with different elastic moduli of the adhesive, layup methods of the shell, and bonding lengths of the skirt. This provides an effective solution for the rational selection of adhesive materials and the rapid assessment of the load-bearing capacity of the skirt connection structure. This is of great significance for improving the bearing capacity of the skirt of the solid rocket motors.