摘要
综述了氢氧、液氧/甲烷两种低温推进剂新型火箭发动机超临界燃烧研究进展。对氢氧火箭发动机、液氧/甲烷火箭发动机超临界燃烧研究的意义、实验研究、仿真研究及超临界燃烧的特点做了介绍,并结合当前的研究提出了一些看法。
Research and development of supercritical combustions in two kinds of cryogenic propellants rocket engines, LOX/H2 and LOX/CH4, is summarized. The research significance, experimental investigations and theoretical simulations of both LOX/H2 and LOX/CH4 rocket engine are introduced, as well as the characteristic of supercritical combustion of cryogenic propellants. Some proposals are given based on current research work.
出处
《导弹与航天运载技术》
北大核心
2009年第6期23-27,共5页
Missiles and Space Vehicles
基金
国家自然科学基金资助项目(50576105)
关键词
低温推进剂
火箭发动机
超临界燃烧
Cryogenic propellant
Rocket engine
Supercritical combustion
