微型脉冲推力器点火启动过程计算与点火药量选择  

Ignition start-up course calculation and ignition charge mass selection of impulse micro-thruster

作　　者：周海清[1] 张平[1] 

机构地区：[1]北京理工大学机电工程学院,北京100081

出　　处：《固体火箭技术》2004年第4期276-279,共4页Journal of Solid Rocket Technology

摘　　要：建立了微型脉冲推力器点火启动模型,模型中考虑了两相流动和颗粒对推进剂表面的冲击传热。根据数值计算结果,给出了不同产物颗粒含量下的点火药量选择参考范围。该参考范围对于产物颗粒含量小于50%的点火药是适用的;由于过多的颗粒含量将对装药表面产生强烈的热力冲蚀破坏作用,产物颗粒含量超过50%的点火药不适合微型火箭发动机。Ignition start-up model of impulse micro-thruster is established, considering two-phase flow and impact heat transfer of particle on the surface of propellant. Based on numerical calculation results, selection range of ignition charge mass with different particle content is given. It is suitable for ignition charge whose particle content is less than 50%. Because excessive particle content can cause strong heat impact failure on the grain surface, ignition charge whose particle content is more than 50% isn't suitable for micro-rocket motor.

关 键 词：微型脉冲推力器 点火药 火箭发动机 推进剂 装药 传热 数值计算 颗粒含量 产物 动模 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程] TQ565.3[化学工程—炸药化工]