火箭推进2018，Vol.44Issue(6)：7-13,7.
3000 N液氧/液甲烷发动机方案与试验研究
Scheme and test of 3 000 N liquid oxygen and liquid methane rocket engine
摘要
Abstract
Liquid oxygen and liquid methane cryogenic propulsion has become one of the most promising chemical propulsion as its advantanges of high specific impulse performance about 350 s, nontoxic, easily integrated main engine and RCE (reaction control engine) and available from local resources on some exploration destination, such as MARS. This paper introduced the developing history of cryogenic liquid oxygen and liquid methane propulsion and the details of the designing and testing methods of the 3 000 N liquid oxygen and liquid methane rocket engine. Engine designing scheme mainly focused on the structure of the injector, cooling, ignition and combustion stability. A hot-fire test of the 3000 N rocket engine was conducted on March 2017, in this test, ignitions of this engine were totally successful, as well as 5 s and 10 s stable tests. As a result, this liquid oxygen and liquid methane rocket engine achieved thrust larger than 2 860 N, combustion efficiencies about 95％ and ground specific impulse larger than 242 s, which are very close to the designed values.关键词
液体火箭发动机/3 000 N/液氧/液甲烷/点火热试车Key words
liquid rocket engine/3 000 N/liquid oxygen/liquid methane/hot-fire test分类
航空航天引用本文复制引用
潘一力,周海清,程诚..3000 N液氧/液甲烷发动机方案与试验研究[J].火箭推进,2018,44(6):7-13,7.基金项目
上海市空间发动机工程技术研究中心资助项目(17DI2280800) （17DI2280800）
