PDF下载 分享
[1]程诚,周海清,田桂,等.液氧/甲烷轨姿控推进系统集成演示试验[J].火箭推进,2023,49(03):56-68.
　CHENG Cheng,ZHOU Haiqing,TIAN Gui,et al.System integration and hot-fire test of liquid oxygen/liquid methane rocket engine for orbit maneuver and attitude control[J].Journal of Rocket Propulsion,2023,49(03):56-68.
点击复制

液氧/甲烷轨姿控推进系统集成演示试验

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 49 期数: 2023年03期 页码: 56-68 栏目: 目次 出版日期: 2023-06-25
Title:
System integration and hot-fire test of liquid oxygen/liquid methane rocket engine for orbit maneuver and attitude control
文章编号:
1672-9374(2023)03-0056-13
作者:
程诚1; 2; 周海清1; 2; 田桂1; 2; 熊靖宇1; 2; 周国峰1; 2; 曾夜明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;  ZHOU Haiqing1; 2;  TIAN Gui1; 2;  XIONG Jingyu1; 2;  ZHOU Guofeng1; 2;  ZENG Yeming1; 2
(1. Shanghai Institute of Space Propulsion, Shanghai 201112, China; 2. Shanghai Engineering Research Center of Space Engine, Shanghai 201112, China)
关键词:
空间推进系统; 液氧/甲烷; 轨控发动机; 姿控发动机; 热试车
Keywords:
space propulsion system;  liquid oxygen/liquid methane;  orbit maneuver engine;  attitude control engine;  hot-fire test
分类号:
V434.1
文献标志码:
A
摘要:
为验证液氧/甲烷轨姿控一体化推进系统涉及的主要关键技术和安全操作流程,上海空间推进研究所研制了国内首款氦气恒压挤压式液氧甲烷推进系统演示样机。历时3年,演示样机于2021年底顺利完成多轮次地面热试车考核,系统运行平稳,轨/姿控发动机工作协调、产品状态良好。介绍了演示样机的设计方案、研制历程和集成演示试验结果,以及轨/姿控发动机的设计与试验情况。液氧甲烷推进系统累计完成48次/约6 000 s系统冷/热态试验考核,配套的5 kN轨控发动机累计完成点火工作40次/1 860 s,配套的150 N/25 N姿控发动机累计完成稳态工作1 690 s/脉冲点火约1 250次。演示样机热试车的成功,标志着我国液氧甲烷空间推进系统实现了从“0”到“1”的突破,为后续型号工程应用奠定了基础,也为我国液体空间动力的升级换代和可持续发展提供了有力支撑。
Abstract:
In order to validate the key technologies and safe operating procedures, the first integrated demonstration prototype of pressure-fed liquid oxygen /liquid methane(LO2/LCH4)propulsion system using helium for orbit maneuver and attitude control in China has been developed by Shanghai Institute of Space Propulsion(SISP)from 2019 for the future in-space vehicles. After 3 years, the demonstration prototype was successfully completed multiple rounds of ground hot-fire tests at the end of 2021, with stable system operation, coordinated engine work and good product condition. The design scheme, development process and test results of the demonstration prototype, as well as the design and test of the orbit/attitude control engine, are introduced in this paper. The integrated propulsion system has performed a total of 48 times/about 6 000 s cold state and hot-fire operations. The 5 kN orbit maneuver engine has completed the hot-fire working for 40 times /1 860 s, and the 150 N and 25 N attitude control engines have completed steady-state hot-fire for 1 690 s /pulse ignition for about 1 250 times. The successful hot-fire tests of the demonstration prototype indicates that the LO2/LCH4 space propulsion system in China has achieved a breakthrough from “0” to “1”, which provides a foundation for the subsequent flight applications and a support for the sustainable development of national liquid space propulsion technology.

参考文献/References:

[1] International Space Exploration Coordination Group(ISECG).The global exploration roadmap[R].NP-2018-01-2502-HQG-327035.
[2] KLEM M,SMITH T,WADEL M,et al.Liquid oxygen/liquid methane propulsion and cryogenic advanced development[R].IAC-11-C4.1.5.
[3] REYNOLDS D C.Oxygen/methane torch igniter design and testing [R].NASA TM-2008-215247.
[4] 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.]:AIAA,2008.
[5] 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.]:AIAA,2010.
[6] 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.]:AIAA,2008.
[7] 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.]:AIAA,2010.
[8] FLACHBART R H,HASTINGS L J,HEDAYAT A,et al.Thermodynamic vent system performance testing with subcooled liquid methane and gaseous helium pressurant[J].Cryogenics,2008,48(5/6):217-222.
[9] JURNS J,MCQUILLEN J.Liquid acquisition device testing with sub-cooled liquid oxygen[C]//44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit.Reston,Virginia:AIAA,2008.
[10] MELCHER J C,MOREHEAD R L.Combustion stability characteristics of the Project Morpheus liquid oxygen/liquid methane main engine[C]//50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2014.
[11] MCMANAMEN J P,HURLBERT E A,KROEGER D.Development and flight operation of a 5 lbf to 20 lbf O2/CH4 roll control engine for Project Morpheus[C]//50th AIAA/ASME/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2014.
[12] HURLBERT E A,ATWELL M J,MELCHER J C,et al.Integrated pressure-fed liquid oxygen/methane propulsion systems:Morpheus experience,MARE,and future applications[C]//52nd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2016.
[13] ATWELL M J,HURLBERT E A,MELCHER J C,et al.Characterization of a pressure-fed LOx/LCH4 reaction control system under simulated altitude and thermal vacuum conditions[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2017.
[14] MOREHEAD R L,MELCHER J C,ATWELL M J,et al.Vehicle-level oxygen/methane propulsion system hotfire demonstration at thermal vacuum conditions[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference.Reston,Virginia:AIAA,2017.
[15] JONES B K,ZANG J C,WEAVER H F,et al.NASA plum brook station test stand in-space propulsion facility test stand characterization hot fire test[C]//2018 Joint Propulsion Conference.Reston,Virginia:AIAA,2018.
[16] Intuitive Machines,LLC.Lunar payload and service:Nova-C lunar lander[EB/OL].https://www.intuitivemachines.com/lunarlander,2021.
[17] CHENG C,ZHOU H Q,PAN Y L,et al.Experimental investigation of 150 N liquid oxygen/liquid methane attitude control engine[R].IAC-17 C4.3.6/x36112.
[18] CHENG C,ZHOU H Q.Experimental investigation of 3 000 N liquid oxygen/liquid methane engine for orbit maneuver[R].SP2018-060.
[19] 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(5):1-9.
CHENG C,QU B,LIN Q G.Overview of integrated cryogenic propulsion system based on liquid oxygen/liquid methane for Morpheus[J].Journal of Rocket Propulsion,2018,44(5):1-9.
[20] 潘一力,周海清,吉林,等.液氧/液甲烷姿控发动机点火技术研究[J].火箭推进,2019,45(4):16-25.
PAN Y L,ZHOU H Q,JI L,et al.Study on ignition technology of LOx/LCH4 attitude control engine[J].Journal of Rocket Propulsion,2019,45(4):16-25.
[21] 程诚,熊靖宇,周国峰,等.NASA液氧甲烷集成推进系统热真空试验[J].火箭推进,2020,46(5):10-20.
CHENG C,XIONG J Y,ZHOU G F,et al.Thermal vacuum test of NASA's integrated LO2/LCH4 propulsion system[J].Journal of Rocket Propulsion,2020,46(5):10-20.
[22] XU W T,CHENG C,SONG X D,et al.Experimental investigation of cryogenic flow quenching of horizontal stainless steel tubes[J].Cryogenics,2021,117:103327.

相似文献/References:

[1]马冬英,卢 钢,张小平,等.液氧/甲烷燃气发生器试验研究[J].火箭推进,2013,39(03):21.
　MA Dong-ying,LU Gang,ZHANG Xiao-ping,et al.Research on hot tests of LOX/methane gas generator[J].Journal of Rocket Propulsion,2013,39(03):21.
[2]陈 庆.空间推进系统可靠性评估方法的改进[J].火箭推进,2012,38(02):49.
　CHEN Qing.Improvement of reliability assessment method for space propulsion system[J].Journal of Rocket Propulsion,2012,38(03):49.
[3]李丹琳,栾叶君,孙纪国.液氧/甲烷气液喷注器试验研究[J].火箭推进,2010,36(04):59.
　Experimental investigation on LOX/CH4 subscale thrust chamber[J].Journal of Rocket Propulsion,2010,36(03):59.
[4]李春红,张小平,马冬英,等.液氧/甲烷燃气发生器点火方案研究[J].火箭推进,2010,36(05):7.
　LI Chun-hong,ZHANG Xiao-ping,MA Dong-ying,et al.Ignition scheme of LOX/methane gas generator[J].Journal of Rocket Propulsion,2010,36(03):7.
[5]张小平,李春红,马冬英.液氧／甲烷发动机动力循环方式研究[J].火箭推进,2009,35(04):14.
　Zhang Xiaoping,Li Chunhong,Ma Dongying.Study on the LOX／methane rocket engine power cycles[J].Journal of Rocket Propulsion,2009,35(03):14.
[6]夏广庆,毛根旺,朱国强,等.美国微波电热推力器的发展历史与研究现状[J].火箭推进,2008,34(04):32.
　Xia Guangqing,Mao Genwang,Zhu Guoqiang,et al.Development history and current research status of the microwave electrothermal thruster in USA[J].Journal of Rocket Propulsion,2008,34(03):32.
[7]仲伟聪.液氧/甲烷液体火箭发动机燃烧研究最新进展[J].火箭推进,2004,(01):52.
[8]程 诚,熊靖宇,周国峰,等.NASA液氧甲烷集成推进系统热真空试验[J].火箭推进,2020,46(05):10.
　CHENG Cheng,XIONG Jingyu,ZHOU Guofeng,et al.Thermal vacuum test of NASA’s integrated LO2/LCH4 propulsion system[J].Journal of Rocket Propulsion,2020,46(03):10.

备注/Memo

收稿日期:2022-10-11; 修回日期:2022-11-15
基金项目:上海市空间发动机工程技术研究中心资助项目(Fc301S-1)
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等。

更新日期/Last Update: 1900-01-01