500 tf级液氧煤油高压补燃发动机研制进展  

Development of 500 tf class high pressure stage combustion LOX/kerosene rocket engine

作　　者：李斌[1] 陈晖[2] 马冬英[2] 高玉闪[2] LI Bin;CHEN Hui;MA Dongying;GAO Yushan(Academy of Aerospace Propulsion Technology, Xi'an 710100, China;Xi'an Aerospace Propulsion Institute, Xi'an 710100, China)

机构地区：[1]航天推进技术研究院,陕西西安710100 [2]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2022年第2期1-10,共10页Journal of Rocket Propulsion

基　　金：国家自然科学基金(51575418)。

摘　　要：500 tf级液氧煤油高压补燃发动机是我国下一代航天主动力,将大幅提升我国航天动力的技术水平,为我国航天发展提供强大动力。发动机采用高压补燃循环系统、泵后摇摆和双推力室方案,具有无毒环保、高性能、高可靠、推力和混合比可调节、使用维护便捷等特点,发动机研制需突破分级启动、健康管理、泵后摇摆、大功率高效涡轮泵、高压大流量高性能燃烧组件、高压大流量调节组件及低温阀门、发动机新工艺与热试验等多项关键技术。目前已完成发动机的方案设计和生产,开展了大量试验验证,完成半系统试车和首台整机装配,关键技术取得重大突破,为发动机后续工程研制奠定了基础。The 500 tf class high pressure stage combustion LOX/kerosene rocket engine is the main power for next-generation rocket.The engine will greatly improve the technical level of rocket engine and provide a strong power for space development in China.In the general design of high pressure stage combustion cycle,swinging after pump and two thrust chambers are adopt.The engine has the characteristics of innocuous,high performance,high reliability,adjustable thrust and mixture ratio,and convenient for use.The key technologies should be breached,including stepped starting,health management,swinging after pump,high-power high-efficiency turbo-pump,high-pressure high-efficiency high-flow-rate combustion subassembly,high-pressure high-flow-rate regulator and low-temperature valve,new product technics and new test.Main development of the engine is that,the design and production of the engine,many experiments,half system tests and production of the first engine have been finished.The key technologies were validated,that lay a foundation for the intending development of the engine.

关 键 词：液体火箭发动机 液氧煤油 大推力 关键技术 半系统试车 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]