摘要
按两类不同的气化速率公式,讨论了固液火箭发动机燃料装药优化设计的方法和程序,并针对某HTPBLOX(或GOX)发动机,给出了多孔装药在不同孔数的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,最后就燃料装药设计和配方设计给出了某些结论。
The method and the procedure of design optimization for fuel grain of hybrid rocket engines were discussed using two different kinds of formula for fuel regression rate With multi port grain of some HTPB/LOX(or GOX) engine the variation of some parameters with time and other parameters were given for different numbers of port Some conclusions were drawn on fuel grain design and fuel ingredient design
出处
《推进技术》
EI
CAS
CSCD
北大核心
2000年第1期67-70,共4页
Journal of Propulsion Technology
关键词
推进剂药柱
配方
最优设计
固液火箭发动机
Hybrid propellant rocket engines,propellant grain
Propellant formulation
Optimization design