摘要
采用颗粒轨道模型进行了含硼贫氧推进剂固体火箭冲压发动机补燃室两相流的数值模拟,其中硼颗粒的点火和燃烧模型采用的是King模型,建立了发动机补燃室内简单反应流模型,并在该模型下对某实验发动机进行了模拟,得出颗粒在补燃室内的分布,结果表明:进入头部回流区的硼颗粒能够快速点火,并且颗粒直径增大后,点火时间增加,颗粒燃烧效率显著降低.
The numerical simulation of two-phase flow in a boron based propellant ducted rocket based on discrete phase model was discussed. The ignition and combustion of boron particles was controlled by King model. Simple reaching flow model was established and used to simulate an experimental motor, and the distribution of particles in the supplementary combustion chamber was obtained. The results show that the particles which go into the dome head recirulation can be ignited easily, and the increase of the particle diameter bring out the ignition time increase. The efficiency will decrease.
出处
《弹道学报》
CSCD
北大核心
2006年第1期68-71,共4页
Journal of Ballistics
关键词
固体火箭冲压发动机
硼颗粒
点火
燃烧
两相流
突扩燃烧室
ducted rocket motor
boron particle
ignition
combustion
two phase flow
side dump combustor
作者简介
胡建新（1975- ）,男,博士研究生,研究方向为火箭发动机过程仿真和火箭冲压发动机.
