Numerical Simulation of Missile Launching from the R/S UAV

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.