Analysis And Numerical Simulation Of A Solid Rocket Booster Flow Field

The flow field of solid rocket booster is very complex, which involves the propellant combustion, mass addition, two phase flow and chemical reaction. As the sub power plant of cruise missile, the booster plays an important role in the initial launching process, the research on the flow field of solid rocket booster should be studied.In this paper, the main research contents of a solid rocket booster are as follows:a) An nozzle structure is obtained by using the principle of hydrodynamic and the nozzle design criterion under design requirements of solid rocket booster. In order to analysis the performance of the nozzle, a two dimensional axisymmetric nozzle model is established and the inviscid and viscous model is carried out by the Fluent software. The influence of different parameters, such as the expansion angle, the contraction angle, the expansion ratio and the throat radius, are analyzed numerically.b)In order to study the ignition process flow field, a two dimensional fluid model considering gas phase ignition model is established. The simulation results show the distributions of the parameters at the different time, such as pressure, temperature and velocity. At the same time, the influence of different factors on the ignition process is studied.c) A two-dimensional combustion chamber and nozzle model is built for further study the engine flow field,and consider to the combustion engine burning surface back-shift and erosive burning phenomenon, establishes the model of erosive burning, by using the dynamic mesh technology and UDF for secondary development. The results obtain the images about the moving burning surface and the variation of the flow field parameters. At last,got a pressure-time curve about the whole process of solid rocket motor based on the research.