Numerical Study On Dual-Pulse Solid Rocket Motor Inner Flow Fields

Dual-pulse solid rocket motor is one of great achievements in scientific research, that belongs to solid rocket motor. There is respective igniter for each pulse propellant grain, which could be ignited respectively. And there are different delays in the time of the second pulse propellant grain ignition. At present, it was solved to the technology of thrust vector control and thrust termination, but there are some problems to be researched further, for example, the material of interstage clapboard, the dimension of interstage port, the flow field characteristic of gas-fired in the first combustion chamber. So the purpose of this paper is to get it.The flow fields of dual-pulse solid rocket motor combustion chamber were simulated. The solution was based on Computational Fluid Dynamics(CFD) software FLUENT6.3 and k-εequations of turbulent model was adopted. Further more, the compressible form of SIMPLE algorithm was applied to gas phase flow field simulation; Discrete Phase Model and PISO algorithm were employed for two-phase flow field simulation.We can get the results from the simulation for the gas flow fields of dual-pulse solid rocket motor. The results are as follows:the changes relationship between gas-fired flow field parameters and the dimension of interstage port, the reasonable number for the diameter of the interstage ports and the combustion chamber lies between 1/3 and 1/2. Then, add discrete phase into gas flow field, by PSIC two phase coupling algorithm. We can educe the characteristic of the particles in different dimension in the first combustion chamber and the influence of gas flow fields for the particles in different percent. At the same time, the adverse influence of two-phase flow to interstage port was analyzed. Theoretical basis was provided for design of the rocket motor and choice of the interstage port.