推进技术 ›› 1989, Vol. 10 ›› Issue (6): 33-37.
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宋连忠
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摘要： 三组元火箭发动机是近几年提出的新概念.本文介绍了三组元推进剂燃烧试验及其结果分析.试验用液氧/丙烷/氢做推进剂在9.78MPa燃烧室压力下完成.试验结果表明,三组元推进剂和三组元发动机概念可行.
关键词: 液体推进剂火箭发动机;多元推进剂;燃烧试验分析
Abstract: Tri-propellant rocket engine is a new concept developed in recent years.The combustion tests of LOX/propane/gas hydrogen tri-propellant are conducted with subscale hardware at chamber pressure of 6.78MPa and the results are analyzed in this paper.It is shown that the concept is feasible.
Key words: Multipropellant;combustion test;Liquid propellant rocket engine;Analyzing
宋连忠. 三组元推进剂燃烧试验分析[J]. 推进技术, 1989, 10(6): 33-37.
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