Abstract: With the development of new high-thrust rockets, the decreasing frequency of the bending modes of the rocket, as well as the factors such as flow separation and shock oscillations generated during transonic flight make it more prone to non-constant vibration. In this paper, a launch vehicle model with boost was taken as the research object, and the aerodynamic damping of the rocket during forced vibration was obtained through numerical calculation. The factors affecting the aerodynamic damping of the rocket were analyzed, including the position of structural nodes, the magnitude of vibration amplitude, pulsating pressure and so on. The study shows that the boost mainly plays the role of increasing aerodynamic damping and the front node mainly affects the aerodynamic damping of the contraction section. The vibration amplitude size and the pulsating pressure have a negligible effect on the aerodynamic damping.