大推力液氧煤油补燃发动机分级起动技术  

Staged Startup Technology of High Thrust Staged Combustion LOX/Kerosene Rocket Engine

作　　者：张晓光[1] 高玉闪[1] 马冬英[1] 蒲星星 陈晖[1] Zhang Xiao-guang;Gao Yu-shan;Ma Dong-ying;Pu Xing-xing;Chen Hui(Xi’an Aerospace Propulsion Institute,Xi’an,710100)

机构地区：[1]西安航天动力研究所,西安710100

出　　处：《导弹与航天运载技术》2020年第4期68-72,共5页Missiles and Space Vehicles

摘　　要：大推力液氧煤油补燃发动机在中国首次采用分级起动技术,以提高发射可靠性。针对发动机分级起动应用需求,开展了分级起动方案论证,提出了起动特性控制的目标和措施,进行了起动特性仿真预示,提出了基于多余度机电伺服系统的起动转级控制方案,建立了起动准备阶段和起动过程多参数融合健康监控方案。发动机半系统试车表明,起动时序和工况参数合理,燃气发生器能量控制措施有效,发动机分级起动方案得到初步验证。The high thrust staged combustion LOX/kerosene rocket engine adopts staged startup technology to improve launch reliability for the first time in China. According to the application requirements of engine staged startup, startup scheme is demonstrated. Control objectives, measures and simulation of starting characteristics are put forward. Redundant electromechanical control scheme for regulators, and multi-parameter fusion health monitor scheme for both startup and its preparation stage are proposed. Engine half-system tests show that start sequence and work parameters are reasonable, and preburner energy control measures are effective. Based on test results, the staged startup scheme is preliminarily validated.

关 键 词：液体火箭发动机 起动 机电伺服 健康监控 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]