补燃循环发动机强迫起动研究  

Research on forced start-up of staged combustion engine

作　　者：杨永强[1] 刘红军[1] 徐浩海[1] 刘站国[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》2011年第2期14-18,共5页Journal of Rocket Propulsion

基　　金：国家航天技术支撑项目

摘　　要：某泵压式液体火箭发动机是我国首台采用强迫起动方式的补燃循环发动机。结合发动机特点建立了强迫起动模型,进行了系统级冷调试验,根据试验及仿真结果确定了发动机起动参数及起动程序。针对试车暴露的问题,采取一系列措施解决了起动超调、起动爆燃、推力室点火冲击大及喷注器起动变形等问题。研究结果在发动机试车中得到验证。The turbopump-fed liquid propellant rocket engine is the first staged combustion cycle engine with forced start-up system in China. A forced start-up simulation model was build, cool-flow system testing was performed, and the start-up parameters and procedure were determined in combination with the characteristics of the engine. The problems appearing in the start-up testing, such as overshoot, deflagration, ignition shock in thrust chamber and injector deformation were solved. The results obtained in the research were validated in engine tests.

关 键 词：液体火箭发动机 补燃循环 强迫起动 仿真分析 试车验证 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]