可贮存推进剂泵压式液体火箭发动机多次起动系统研究  

Study on the multi-start system of turbopump-fed rocket engine with storable propellants

作　　者：张涛[1] 唐虎[1] 周江平[1] 董创华[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2010年第3期15-18,共4页Journal of Rocket Propulsion

摘　　要：在推力超过一定量级、任务时间较长的情况下,泵压式发动机比挤压式发动机具有明显的技术优势。从国内外上面级及重型空间飞行器推进系统的发展需求来看,均要求其主发动机具有多次起动工作的能力。针对采用可贮存推进剂的泵压式液体发动机多次起动需求,对几种可选的多次起动系统方案进行了比较分析,介绍了起动箱式起动系统的研究情况。For high level thrust requirement and long duration mission, the turbopump-fed rocket engine has more advantages than that of the pressure-fed rocket engine. To meet the need of the development of propulsion system for upper stage and heavy space vehicle, the engine should have the capability of multi-start. This paper aimed at the need for the multi-start capability of the storable propellant turbopump-fed rocket engine. Several different designs of the multi-start system were analyzed and efforts on the start-tank system development were described.

关 键 词：泵压式 火箭发动机 多次起动 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]