三组元液体火箭发动机系统方案研究

推进技术 ›› 1997, Vol. 18 ›› Issue (3): 5-9.

三组元液体火箭发动机系统方案研究

钟家强,胡平信

北京丰源机械研究所!北京;100076;北京丰源机械研究所!北京;100076

发布日期:2021-08-15

A STUDY ON SCHEMES OF TRIPROPELLANT LIQUID ROCKET ENGINES

Beijing Fengyuan Machinery Iust., Beijing, 100076;Beijing Fengyuan Machinery Iust., Beijing, 100076

Published:2021-08-15

摘要/Abstract

摘要： 三组元发动机是实现单级入轨的一项关键性技术。虽然国外从70年代就开始研究双燃烧室的三组元发动机,但由于推力室结构过于复杂,至今尚无一台样机出现。这里提出的三组元发动机系统,建立在三组元喷嘴技术基础之上,充分继承了已有的液氢／液氧、液氧／煤油发动机的研制成果,是技术先进、性能高、可在短期内实现的液体火箭发动机。

关键词: 推进系统;航天飞机主发动机;三元推进剂;方案研究

Abstract: It is necessary to develop fully reusable single-stage-to-orbit (SSTO) vehicles todramatically decrease the cost of transporting cargo and men into orbit, because the cost is tooexpensive by expandable vehicle. Tripropellant liquid rocket engine (TLRE) is a critical technique inSSTO vehicles. Although TLRE with dual combustion chamber (Dual-Expander, Dual-Throat) hasbeing studied since 70’s, up to now no engine appears because of too complicated structure of thecombustion chamber. Based on the technique of tripropellant injector developed by our institute, thepaper presents a new designed TLRE with advanced performance which takes achievements of LH/LO & LO/RP-1 engines into accout and can be realised in near future.

Key words: Propulsion system;Space shuttle main engine;Tripropellant;Proposal study

钟家强,胡平信. 三组元液体火箭发动机系统方案研究[J]. 推进技术, 1997, 18(3): 5-9.