颗粒传热增强对微型脉冲推力器点火过程的影响  

Effect of particle heat transfer enhancement on ignition process of miniature impulse thruster

作　　者：周海清[1] 尤政[1] 张平[2] 

机构地区：[1]清华大学精密仪器与机械学系,北京100084 [2]北京理工大学机电工程学院,北京100081

出　　处：《固体火箭技术》2006年第1期31-34,共4页Journal of Solid Rocket Technology

基　　金：国家部委重点预研项目(10403010203)

摘　　要：为了分析点火药产物中炽热颗粒对固体脉冲推力器点火过程的影响,采用了颗粒对壁面的冲击热增强模型来模拟炽热颗粒对推进剂表面的传热增强效应,进行了微型脉冲推力器点火过程的数值分析。结果表明,颗粒热增强效应显著影响脉冲推力器的点火启动过程,颗粒的热增强效应显著缩短了点火延迟时间,并使点火启动过程的压强增大,点火过程对颗粒含量较少的点火药更敏感;设计微型脉冲推力器点火器时要严格匹配产物颗粒含量,并严格控制点火药量范围。In order to analyze the effect of hot particle in ignition charge product on ignition process of miniature impulse thruster,a particle impact heat enhancement model was used to simulate the effect of hot particle on heat transfer enhancement of propellant surface ;the ignition process of miniature impulse thruster was numerically analyzed. The results show that the particle heat enhancement significantly affects the ignition starting process, shortens ignition delay time and makes pressure during the ignition starting process increase;the ignition process is more sensitive to ignition charge with less particle content. It is necessary to control the particle content in the product and the amaunt of ignition charge strictly in design of the miniature impulse thruster.

关 键 词：微型脉冲推力器 点火 颗粒传热增强 两相流 数值分析 

分 类 号：V435.14[航空宇航科学与技术—航空宇航推进理论与工程]