|Table of Contents|

Scheme and test of 3000 N liquid oxygen and liquid methane rocket engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2018年06期
Page:
7-13
Research Field:
研究与设计
Publishing date:

Info

Title:
Scheme and test of 3000 N liquid oxygen and liquid methane rocket engine
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
Keywords:
liquid rocket engine;  3 000 N;  liquid oxygen;  liquid methane;  hot-fire test
PACS:
V434-34
DOI:
-
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.

References:

[1] NASA's Exploration Systems Architecture Study Final Report: NASA-TM-2005-214062[R].USA:NASA,2005.
[2] 李斌,张小平,高玉闪.我国可重复使用液体火箭发动机发展的思考[J].火箭推进,2017,43(1):1-7.
LI B, ZHAN X P, GAO Y S.Consideration on development of reusable liquid rocket engine in China[J].Journal of rocket propulsion,2017, 43(1):1～7.
[3] 孙宏明.液氧/甲烷发动机评述[J].火箭推进,2006,32(2):23-31.
SUN H M.Review of fluid oxygen/methane rocket engine[J].Journal of rocket propulsion,2006,32(2):23-31.
[4] 王少鹏.21世纪空间运输系统的液氧\甲烷火箭发动机[J],火箭推进,2002,28(1):50-54.
WANG S P.21st century space transportation system using liquid oxygen/methane rocket engine[J].Journal of rocket propulsion, 2002,28(1):50-54.
[5] TIMOTHY D, WADEL M F.Liquid oxygen/liquid methane propulsion and cryogenic advanced development [C]// International Aerospace Conference.[S.I.]: [s.n.],2008.
[6] HART J.Verticaltest bed flight testing: NASA–TM-2014 [R].USA: NASA, 2014.
[7] OLANSEN J B, MUNDAY S R.Projectmorpheus: lander technology development [C]//AIAA space conference and exposition.USA:AIAA,2014.
[8] 王维彬,孙纪国.航天动力发展的生力军——液氧甲烷火箭发动机[J].航天制造技术,2011(2):3-6.
[9] HERLBURT E, ANGSTADT T.870 lbf reaction control system tests using LOX/ethanol and LOX/methane at white sands test facility[C] //44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.USA:AIAA, 2008.
[10] ROBINSON P J, VEITH E M, LINNE D L,et al.Conceptual design of a 5,500-lbf LOX/LCH4 lunar ascent main engine[C] // 4th JANNAF Liquid Propulsion Subcommittee Meeting.USA:[s.n.],2008.

Memo

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Last Update: 2018-12-25