渐变式三组元发动机实现单级入轨的最优控制

推进技术 ›› 2003, Vol. 24 ›› Issue (6): 488-490.

渐变式三组元发动机实现单级入轨的最优控制

谭建国,徐万武,王振国

国防科技大学航天与材料工程学院湖南长沙410073;国防科技大学航天与材料工程学院湖南长沙410073;国防科技大学航天与材料工程学院湖南长沙410073

发布日期:2021-08-15
基金资助:
国家“八六三”基金项目资助 (863 2 3 4 8)

Optimal control analysis on gradual tripropellant engine for SSTO

Inst. of Aerospace and Material Engineering, National Univ. of Defense Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defense Technology, Changsha 410073, China;Inst. of Aerospace and Material Engineering, National Univ. of Defense Technology, Changsha 410073, China

Published:2021-08-15

摘要/Abstract

摘要： 通过对推进剂组分进行连续控制,渐变式三组元发动机能够很好地满足单级入轨对比冲和密度比冲的要求。建立这种新概念发动机实现单级入轨的控制方程,得到了液氢燃料比和余氧系数的变化规律。结果表明:渐变式三组元发动机比传统双模式发动机或渐变式氢氧发动机的性能分别高25%和11%。

关键词: 液体推进剂火箭发动机;三元推进剂;单级入轨;推进剂控制

Abstract: Gradual engine can meet the needs of specific impulse and density specific impulse of single stage to orbit （SSTO） because the propulsion combination was changed gradually. The control equations of gradual tripropellant engine for SSTO were established. The variation law was attained for excess oxygen coefficient and hydrogen-fuel ratio by solving the equations. Results show that performance of gradual tripropellant engine was 25% higher than that of traditional tripropellant engine and 11% higher than that of gradual LOX/LH₂ engine.

Key words: Liquid propellant rocket engine;Tripropellant;Single-stage-to-orbit;Propellant control

谭建国,徐万武,王振国. 渐变式三组元发动机实现单级入轨的最优控制[J]. 推进技术, 2003, 24(6): 488-490.