The transonic aerodynamic damping characteristics of a rocket model is analyzed by the coupled iterations of computational fluid dynamics （CFD）/computational structural dynamics （CSD）.The unsteady aerodynamic forces on a rocket model are obtained by solving the Navier-Stokes （N-S）equations，the structural dynamic responses are achieved by the modal superposition method，and the data transfer between the solid and fluid domains are realized by the inversed distance interpolation technique.The efficient kD-tree data structure is used to find the nearest neighbors for fluid wall nodes，which improves the interpolation efficiency greatly.The numerical simulation results have a consistent trend with the wind tunnel test results，which illustrates the effectiveness of the numerical algorithm in this paper.The work in this paper can be used for rapid evaluation in the model development plan stage.Compared with conventional aerodynamic damping wind tunnel testing，it can significantly speed up the model development process.Finally，regarding the deviation between the simulation value and the experimental value，this paper analyzes the reasons for the deviation from three perspectives：computational model processing，simulation algorithm and dynamic characteristics，pointing out the direction for subsequent improvement of simulation accuracy.