Simulation of the Influence of Missile Exhaust Plume to the Launching Equipment

To study the variation pattern of pressure and temperature on the launching equipment during the launching process, finite volume method was used to calculate three-dimensional unsteady flow field during the launching process. The zone moving and dynamic laying update method were used to simulate the flow field at the instant of ignition, missile moving to 2 m, 4 m, 6 m and 10 m in the launch canister, missile moving to 5 m, 10 m, 20 m and 25 m out of the launch canister. The open time of back fragile cap, the aerodynamic loads and temperature distribution on the flame deflector, launch canister, adjacent launch canister, front cap and back cap. The analysis on the calculation results provides some meaningful reference to the launching platform design.