带簇式推力室的固液火箭发动机装药设计  

Grain design for hybrid rocket engine with cluster type thrust chamber

作　　者：曹泰岳[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2000年第3期60-62,共3页Journal of Propulsion Technology

摘　　要：讨论了带簇式推力室的固液火箭发动机多孔装药的设计方法 ,并针对某 HTPB/ L OX(或 GOX)发动机给出了不同推力室数和不同孔数情形下某些参数随时间的变化 ,以及另一些参数的总体值或平均值 ,表明簇式推力室方案是可行的 。The method of design for multi port fuel grain of hybrid rocket engines with cluster type thrust chambers was discussed for different numbers of thruster chambers and grain ports As an example, the variation of some parameters with time and the overall or average values of other parameters was given for some HTPB/LOX(or GOX) engine It is showed that cluster type thrust chamber scheme is feasible and it is necessary to develop the solid fuel ingredient which is suitable to hybrid rocket engines

关 键 词：混合推进剂火箭发动机 簇式推力室 装药设计 

分 类 号：V436[航空宇航科学与技术—航空宇航推进理论与工程]