摘要
研究了氢氧变混合比以及三组元发动机在单级入轨飞行器上的应用，包括了普通固定膨胀比发动机和塞式发动机。依据最优弹道计算，分别讨论了燃料混合比控制方案以及组元分配方案。分析了燃料混合比连续可变时的飞行器性能，克服了以往分析中只设定两种混合比及分析过于理想化的问题。
The variable mixture ratio hydrogen fuel rocket and tripropellant engine for SSTO were discussed.The ordinary and aeropike engines were discussed too.In previous works,some were made too many simplification and some were only analysed dual mixture ratio rocket,so they couldn′t reflect the influence made by variable mixture ratio rocket really.We discuss the optimal mixture rutio process during ascent based on trajectory optimization.The percents of propellant when using tripropellant engine were also discussed.The simplification made in analysis is reasonable
出处
《推进技术》
EI
CAS
CSCD
北大核心
1998年第5期1-5,共5页
Journal of Propulsion Technology
关键词
单级入轨
氢氧发动机
混合比
三元推进剂
Single stage to orbit,Hydrogen oxygen engine,Propellant mixture ratio,Tripropellant
