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[1]程诚,曲波,林庆国.Morpheus液氧/甲烷一体化推进系统研究综述[J].火箭推进,2018,44(05):1-9.
　CHENG Cheng,QU Bo,et al.Overview of integrated cryogenic propulsion system based on liquid oxygen/liquid methane for Morpheus[J].Journal of Rocket Propulsion,2018,44(05):1-9.
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Morpheus液氧/甲烷一体化推进系统研究综述

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 44 期数: 2018年05期 页码: 1-9 栏目: 专论与综述 出版日期: 2018-10-31
Title:
Overview of integrated cryogenic propulsion system based on liquid oxygen/liquid methane for Morpheus
文章编号:
1672-9374(2018)05-0001-09
作者:
程诚1; 2; 曲波1; 2; 林庆国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):
CHENG Cheng1;  2;  QU Bo1; 2;  LIN Qingguo1;  2
1.Shanghai Institute of Space Propulsion, Shanghai 201112, China; 2.Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China
关键词:
星球着陆器;  空间推进系统;  液氧/甲烷;  发动机;  Morpheus着陆器
Keywords:
planet lander;  space propulsion system;  liquid oxygen/liquid methane;  engine;  Morpheus lander
分类号:
V434.1-34
文献标志码:
A
摘要:
液氧/甲烷推进剂组合凭借其比冲性能、绿色无毒、空间贮存特性及原位资源利用等综合性能高的优势,被NASA选定为未来化学空间推进的主要发展方向。Morpheus着陆器顺利在肯尼迪航天中心完成自由飞行与自主着陆试验,标志着NASA的液氧/甲烷空间推进技术达到了从单项技术开发走向系统集成应用的新里程碑。介绍了Morpheus着陆器的研制历程与研发模式,针对其采用的液氧/甲烷轨姿控一体化推进系统,详细介绍了系统构成、推进剂输送方案和供应管路热控方案,以及可变推力主发动机和滚动控制发动机的设计原则、研制历程、涉及的主要技术问题与解决措施等。
Abstract:
Liquid oxygen/liquid methane(LO2/LCH4)was choosed as main developing direction for future chemical space propulsion, because of its advantages at specific pulse, green and non-toxic, easy to storage in space, in-situ resource utilization and etc.Successful free flight and autonomous landing of the Morpheus lander in Kennedy Space Center indicates that NASA's liquid oxygen /liquid methane(LO2/LCH4)space propulsion technologies have reached the new milestones from single technology development to system integration application.The development process and research mode of Morpheus lander are introduced in this paper.For the integrated LO2/LCH4 propulsion system, the composition, propellant feeding scheme and thermal control method of feeding lines are discussed in detail.Besides, the design principle, development process, major technical issues and their solutions of the main engine with variable thrust and rolling control engine are also investigated in this paper.The results are valuable for development of the advanced cryogenic propulsion system of future planet landers.

参考文献/References:

[1] Anon.NASA's exploration systems architecture study: NASA–TM-2005-214062 [R].USA: NASA, 2005.
[2] MARK D K.Liquid oxygen / liquid methane propulsion and cryogenic advanced development: IAC-11-C4.1.5 [R].[S.l.]: IAC, 2011.
[3] REYNOLDS D C.Oxygen/methane torch igniter design and testing: NASA TM-2008-215247 [R].USA: NASA, 2008.
[4] BREISACHER K, AJMANI K.LOX/methane main engine igniter tests and modeling: AIAA 2008-4757 [R].USA: AIAA, 2008.
[5] 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.[S.l.]:[s.n.], 2008: 10-19.
[6] ELAM S K, SPRAD E R.Test report for test program P7061: liquid oxygen / liquid methane demonstration with coaxial injectors: NASA TM-2009-215743 [R].USA: NASA, 2009.
[7] ELAM S K, SPRAD E R.LOX / LCH4 technology demonstration-P8006A: NASA TM-2009-216268 [R].USA: NASA, 2009.
[8] STIEGEMEIER B, WILLIAMS G, MELCHER J C, et al.Altitude testing of an ascent stage LOX / methane main engine [C]// 5th JANNAF Liquid Propulsion Subcommittee Meeting.[S.l.]:[s.n.], 2010: 111-120.
[9] TRINIDAD M A, DRESSLER G A, STUDAK J W.An update on the development of NGC's TR408: 100-lbf LOX/LCH4 reaction control engine [C]// 4th JANNAF Liquid Propulsion Meeting.[S.l.]:[s.n.], 2008: 145-152.
[10] ROBINSON P J, VEITH E M, DAMICO S J, et al.Development summary of a 100-lbf LOX/LCH4 reaction control engine [C]// 4th JANNAF Liquid Propulsion Meeting.[S.l.]:[s.n.], 2008: 101-108.
[11] STIEGEMEIER B, MARSHALL W.Sea-level testing of a 100 lbf LOX/methane reaction control engine [C]// 5th JANNAF Liquid Propulsion Subcommittee Meeting.[S.l.]:[s.n.], 2010: 50-57.
[12] MARSHALL W, KLEINHENZ J.Hot-fire testing of 100 lbf LOX/LCH4 reaction control engine at altitude conditions [C]// 5th JANNAF Liquid Propulsion Subcommittee Meeting.[S.l.]:[s.n.], 2010: 24-29.
[13] BARSI S, MODER J, KASSEMI M.Numerical investigation of LO2 and LCH4 storage tanks on the lunar surface: AIAA 2008–4749 [R].USA: AIAA, 2008.
[14] FLACHBART R, HASTINGS L, HEDAYAT A, et al.Thermodynamic vent system performance testing with subcooled liquid methane and gaseous helium pressurant [J].Cryogenics 2008, 48:217-222.
[15] JURNS J, MCOUILLEN J.Liquid acquisition device testing with sub-cooled liquid oxygen [C]// AIAA 44th Joint Propulsion Conference.[S.l.]: AIAA, 2013: 123-129.
[16] ZIMMERLI G, ASIPAUSKAS M, WAGNER J, et al.Propellant quantity gauging using the radio frequency mass gauge: AIAA 2011-1320 [R].USA: AIAA, 2011.
[17] JON B O, STEPHEN R M, JENNIFER L D.Project morpheus: lander technology development: AIAA 2014-4314 [R].USA: AIAA, 2014.
[18] JENNIFER L D, JON B O.Project morpheus: tailored systems engineering of a terrestrial flight testbed for maturing NASA lander technologies: AIAA 2015-0849 [R].USA: AIAA, 2015.
[19] ERIC H, ROBERT M, JOHN C M,et al.Integrated pressure-fed liquid oxygen/methane propulsion systems: Morpheus experience, MARE, and future applications: AIAA 2016-4681[R].USA: AIAA, 2016.
[20] MOREHEAD R L, ATWELL M J, MELCHER J C, et al.Cold helium pressurization for liquid oxygen / liquid methane propulsion systems: fully-integrated initial hot-fire test results: AIAA 2016-4682 [R].USA: AIAA, 2016.
[21] MELCHER J C, ATWELL M J, MOREHEAD R L, et al.Coil-on-plug ignition for LOX/methane liquid rocket engines in thermal vacuum environments [C]// AIAA, SAE/ASEE Joint Propulsion Conference.[S.l.]: AIAA, 2017: 18-25.
[22] MOREHEAD R L, MELCHER J C, ATWELL M J, et al.Integrated cryogenic propulsion test article hot fire testing [R].USA: NASA, 2017.
[23] MOREHEAD R L, ATWELL M J, HURLBERT E A.Cold helium gas pressurization for spacecraft cryogenic propulsion systems [R].USA: AIAA, 2017.
[24] ATWELL M J, HURLBERT E A, MOREHEAD R L, et al.Pressure-fed cryogenic reaction control system for spacecraft: transient system modeling and hot fire test results [R].USA: AIAA, 2017.
[25] JENNIFER L D, JON B O, STEPHEN R M.Project morpheus: Morpheus 1.5A lander failure investigation results: AIAA 2013-5358 [R].USA: AIAA, 2013.
[26] JON B O, STEPHEN R M, JENNIFER L D.Project Morpheus: lessons learned in lander technology development: AIAA 2013-5310 [R].USA: AIAA, 2013.
[27] JON B O, STEPHEN R M, JENNIFER L D.Project Morpheus: lander technology development: AIAA 2014-4314[R].USA: AIAA, 2014.
[28] JENNIFER L D, JON B O.Project Morpheus: tailored systems engineering of a terrestrial flight testbed for maturing NASA lander technologies: AIAA 2015-0849 [R].USA: AIAA, 2015.
[29] ROBERT L M.Project Morpheus main engine development and preliminary flight testing: AIAA 2011-5927[R].USA: AIAA, 2011.
[30] JOHN C M, ROBERT L M.Combustion stability characteristics of the project morpheus liquid oxygen/ liquid methane main engine: AIAA 2014-3681 [R].USA: AIAA, 2014.
[31] HURLBERT E A, MCMANAMEN J P, STUDAK J W.Advanced development of a compact 5-15 lbf LOx/methane thruster for an integrated reaction control and main engine propulsion system: AIAA 2011-6113 [R].USA: AIAA, 2011.
[32] MCMANAMEN J P, HURLBERT E A.Development and flight operation of a 5 lbf to 20 lbf O2/CH4 roll control engine for project Morpheus: AIAA 2014 -3589 [R].USA: AIAA, 2014.

备注/Memo

收稿日期:2018-04-16
作者简介: 程 诚(1987—),男,博士,高级工程师,研究领域为空间推进技术

更新日期/Last Update: 1900-01-01