Numerical Study on Ignition Transient Process of Solid Rocket Motor Based on Ignition Particle

In order to study the flow and combustion characteristics of ignition particles in the combustion chamber during SRM ignition, based on the N-S equation and the k-ε turbulence model, and using the discrete phase model + UDF interface program, numerical simulation analysis of the ignition transient process of a SRM was made. The calculation results show that during the ignition process of the SRM, the ignition powder particles reacted in a chain. The ignition powder particles reacted violently after being injected into the combustion chamber, which was beneficial to the ignition of the propellant and shortened the ignition delay time. The movement of ignition particles in the combustion chamber was complex. Pressure oscillation, local high temperature region and difference between internal and external pressures occurred in the flow field of the SRM. These phenomena varied with the amount of ignition and had a great influence on the propellant ignition and the structural integrity of the propellant. The research results can provide reference for the ignition design of SRM.