Solid Rocket Launch A Pilot In The Exhaust Flow Field Characteristics Research

During the time when a solid rocket motor with a tail-pipe nozzle works, ablation takes place in the tail-pipe nozzle insulator for the impact of gas-solid flow of high temperature and high velocity. Therefore, severe ablation takes place in the inner wall of solid rocket motor with a tail-pipe nozzle. With the continuous increase of the ablation, the inner wall is also changing, and in the nozzle flow field will continue to change, and serious discrepancies with the design parameters, greatly affecting the normal working of the solid rocket motor. Thus,by analyzing the flow field inside the nozzle,it is essential for optimizing the structure of the thermal protection.This thesis for a solid rocket motors with tail-pipe nozzle, by numerical simulation, we can get the pure gas flow field and gas-solid flow field of the tail-pipe nozzle. The research says:1.To establish a physical model of the pure gas phase flow field about the tail-pipe nozzle of solid rocket motors. Set the initial boundary, using k-s turbulence model to calcualte the physical model of the pure gas turbulence. We get viscous and inviscid flow field of the tail-pipe nozzle in the pure gas phase flow, and also get some important parameters of the flow field, for example temperature, pressure and Mach number. This is a good foundation for further research.2. To establish of a physical model of the two-phase flow field about the tail-pipe nozzle of solid rocket motors. Set the initial conditions, then calcualtes to get the gas-solid flow field. Study the impact of the flow field, when changes size of gas particle, and analysis of the variation.In this paper, the work and results provide some values for the design and application of a solid rocket motor, at the same time provide a reference for further study.