The thesis simulates the missile launch process by the method of the computational fluid dynamics (CFD), in order to study the aerodynamic interference and the rules of missile movement. A moving chimera grid approach is used coupled with an unsteady Euler flow solver, and a 6-DOF model is fully integrated into the CFD solution procedure to determine the body dynamics. And the paper presents the results obtained for a time-accurate missile launching from the R/S UAV by the developed numerical methods. Major trends of the separation are captured. As a result, the application shows the validity of moving chimera grid method, the use of the method of the CFD and the technology of moving chimera grid give a reference and gist to the study of the process of missile launch. The computation result shows that the effect of aerodynamic interference due to the thrust is negligible.