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

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