基于点火药颗粒的固体火箭发动机点火瞬态过程数值研究

为研究固体火箭发动机点火时点火药颗粒在燃烧室内流动与燃烧特性，以N-S方程，k-ε湍流模型为基础，采用颗粒轨道模型+UDF接口进行二次开发编程，对某型固体火箭发动机点火瞬态过程进行数值仿真分析.计算结果表明:发动机点火过程中，点火药颗粒呈链式反应；点火药颗粒在喷入燃烧室后迅速燃烧，有利于推进剂点火，缩短点火延迟时间；点火药颗粒在燃烧室内运动复杂，在发动机内流场中出现压强震荡、局部高温区域和内外通压强差等复杂现象，这些现象随点火药量的不同而变化，对推进剂点火、药柱结构完整性产生较大的影响. 

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.