Computational Study On Dynamic Performance Of Gas-Steam Launching System

In this article, submarine-to-ground missile's launch interior ballistic was researched on the background of the launch technologies were deeply understood and a supposed gas-steam launch system was be used as physical model. Firstly, the discrete phase scheme was used to simulate the flow condition, water droplet evaporating rate and droplet flow trail in the cooler. The pressure field, temperature field, velocity field and the effects of continuous phase's velocity, temperature and droplet's diameter on evaporating rate were analyzed. Secondly, the dynamic grid model and species transport model were used to stand the calculation model of missile interior ballistic which use the User Define Program to define the inlet boundary condition and missile moving law. The missile interior ballistic had been calculated with the experimental data. The pressure field, temperature field and missile moving law in launch canister had been given by the calculation. Then the works as below had been done.(1) Adjust the gas' mass fraction, calculate the influent of gas's mass fraction on missile interior ballistic and flow condition in launcher canister;(2) Adjust the inlet angle, calculate the influent of inlet angle on missile interior ballistic and flow condition in launcher canister;(3) Calculate the heat loss through launch canister wall and the influent of heat loss on missile interior ballistic.The calculation results showed that the gas' mass fraction increase made the leaving canister velocity increase and leaving canister time decrease; when the inlet angle were 45°and 60°, the interior ballistic were basically same, when the inlet angle was 90°, the leaving canister time was a little long and the leaving canister velocity was a little big; the heat loss through launch canister wall was little, the interior ballistic almost wasn't impacted by it. The leaving canister velocity and leaving canister time were compared well from calculation and experiment. This calculation method and data can be used in design of the missile launch system interior ballistic.