The flow field of the concentric canister launcher and structural optimization was simulated numerically based on the axisymmetric Navier-Stokes(N-S)equation

the k-ω shear stress transfer (SST) turbulence model and the dynamic mesh update method named zone moving and dynamic laying. With reference to the initial scheme of the concentric canister launcher

the dynamic flow field of the launching process was studied. On this basis

the parameterization of the convergence angle of the convergent section of the inner cylinder and the expansion angle of the expansion section of the cylinder was studied. The results showed that the convergent section of the inner cylinder made the gas discharge guide smoother

the thermal environment inside the cylinder was improved

and the inner cylinder convergence section played a certain role of anti-spray. The larger convergence angle brought about the better thermal environment at the bottom of the cylinder. The expansion section of the nozzle had a significant change to the dynamic flow field during the launch process. When the convergence angle was 15 degrees and the expansion angle was 20 degrees

the thermal environment of the missile was the best from the start to the complete exit.