摘要
为了获取大推力氢氧发动机推力室设计的相关准则和经验,通过对比分析国外典型大推力氢氧发动机推力室的技术方案,总结了喷注器、主燃烧室和喷管延伸段等组合件关键设计参数和结构方案的选择规律,以及工艺方法和材料应用的发展趋势,可为中国未来200 t级大推力氢氧发动机推力室方案的确定提供相应的设计参考。
In order to obtain design criterion and practical experience, the current technology of foreign large LOX/LH2 thrust chamber is reviewed. The laws of key design and structure parameters selection of injectors, combustion chamber and nozzle extension are summarized as well as the future development trend of production technology and material application, which gives the design reference to China future 200 t large LOX/LH2 thrust chamber.
出处
《导弹与航天运载技术》
北大核心
2012年第4期27-30,38,共5页
Missiles and Space Vehicles
关键词
氢氧发动机
推力室
技术方案
对比分析
LOX/LH2 rocket engine
Thrust chamber
Technical schemes
Comparative analysis
