膨胀循环发动机低温起动特性研究  

Research on the Start-up Characteristics of Expander Cycle Engine with a Colder Thrust Chamber

作　　者：王珏[1] 孙慧娟[2] 刘恒[2] 李锦江[2] Wang Jue;Sun Hui-juan;Liu Heng;Li Jin-jiang(China Academy of Launch Vehicle Technology,Beijing,100076;Beijing Aerospace Propulsion Institute,Beijing,100076)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]北京航天动力研究所,北京100076

出　　处：《导弹与航天运载技术》2021年第6期7-11,共5页Missiles and Space Vehicles

摘　　要：某氢氧发动机采用闭式膨胀循环,并采取箱压自身起动方式,最初的起动能源是经过结构尤其是以推力室冷却夹套为主的金属热容加温后的气氢,在贮箱压力确定的情况下,结构温度影响发动机起动特性,温度越低,起动能量越小,进而影响发动机起动可靠性。对发动机起动瞬态特性与推力室结构温度的关联性进行仿真分析与试验验证,获得膨胀循环发动机低温起动特性。A LOX/LH2 rocket engine chose the closed expander cycle.The start-up of the engine is a self start-up process under the tank pressure.The original power for start-up comes from the heat transfer with hardware,mostly with the thrust chamber.When the tank pressure is constant,the temperature of hardware is an important factor in the start-up characteristics of the engine.The colder the thrust chamber,the lower power used to drive the turbo-pump.The engine may be unable to start.The relationship of start-up characteristics and temperature of the thrust chamber is reached.The simulation analysis and experiment are carried out.The start-up characteristic of expander cycle engine with a colder thrust chamber is obtained.

关 键 词：氢氧发动机 闭式膨胀循环 结构温度 起动 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]