Abstract: This paper aims at evaluating the thermodynamic environment of concentric canister launcher system. Based on the 3D Reynolds average conservation Navier-Stokes equations, component transport model and dynamic mesh update method, numerical calculation model of concentric canister launcher system was established. The validity of the numerical simulation model was verified by launching tests with 1:1 prototype launcher. The influence of adapter (also called lateral damping support system) and contraction section on the thermal environment of gas flow field was analyzed by simulating the 3D unsteady flow field of concentric canister launcher of different structures. The numerical results and experimental results showed the thermal shock effect and variation law of gas flow on guiding cone, launching barrel, missile, etc. The results indicate that the adapter and the contraction section have a great influence on the thermodynamic environment of missile launching. The research results provide a reliable theoretical basis for further study of thermodynamic environmental influence on dynamic response with concentric canister launchers.