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[1]潘一力,周海清,程 诚.3000N液氧/液甲烷发动机方案与试验研究[J].火箭推进,2018,44(06):7-13.
　RAN Yili,ZHOU Haiqing,CHENG Cheng.Scheme and test of 3000 N liquid oxygen and liquid methane rocket engine[J].Journal of Rocket Propulsion,2018,44(06):7-13.
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3000N液氧/液甲烷发动机方案与试验研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 44 期数: 2018年06期 页码: 7-13 栏目: 研究与设计 出版日期: 2018-12-31
Title:
Scheme and test of 3000 N liquid oxygen and liquid methane rocket engine
文章编号:
1672-9374(2018)06-0007-07
作者:
潘一力1; 2; 周海清1; 2; 程 诚1; 2
1.上海空间推进研究所,上海 201112; 2.上海空间发动机工程技术研究中心, 上海 201112
Author(s):
RAN Yili1; 2;  ZHOU Haiqing1; 2;  CHENG Cheng1; 2
1.Shanghai Institute of Space Propulsion, Shanghai 201112, China； 2.Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China
关键词:
液体火箭发动机;  3 000 N;  液氧;  液甲烷;  点火热试车
Keywords:
liquid rocket engine;  3 000 N;  liquid oxygen;  liquid methane;  hot-fire test
分类号:
V434-34
文献标志码:
A
摘要:
液氧/液甲烷以其高性能、无毒、易于轨姿控一体化、行星表面资源原位利用等优势已成为国际化学空间推进的主流发展方向之一,对国内外低温液氧甲烷化学空间推进发展和3 000 N液氧甲烷发动机的方案设计和试验研究进行了介绍。方案主要包括总体结构方案,喷注方案、冷却方案、点火方案和燃烧稳定性分析。3 000 N发动机于2017年3月进行了点火热试车,发动机点火全部取得成功,并进行了5 s和10 s稳态试验。燃烧效率约0.95,推算推力大于2 860 N,地面比冲大于242 s,与设计指标基本相当。
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, non-toxic, 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 3 000 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.

参考文献/References:

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备注/Memo

收稿日期:2018-09-01; 修回日期:2018-10-29 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) 作者简介: 潘一力(1987—),男,硕士,研究领域为液体火箭发动机、推进系统设计

更新日期/Last Update: 2018-12-25