渐变式三组元发动机实现单级入轨的最优控制  

Optimal control analysis on gradual tripropellant engine for SSTO

作　　者：谭建国[1] 徐万武[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《推进技术》2003年第6期488-490,504,共4页Journal of Propulsion Technology

基　　金：国家"八六三"基金项目资助 (863 2 3 4 8)

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%。Gradually changing engine can meet the needs of specific impulse and density specific impulse for single stage to orbit (SSTO) because the propulsion components are controlled in a consecutive way. Through building the control equations for this new idea engine to realize single stage to orbit, we get the changing law for liquid hydrogen fuel's proportion and excess oxygen coefficient by solving the equations. Results show that performance of gradually changing tripropellant engine is 25% higher than that of traditional tripropellant engine and 11% higher than that of gradual LOX/LH2 engine.

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 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]