第二代490N轨控发动机研制及在轨飞行验证

doi:10.13675/j.cnki. tjjs. 190343

推进技术 ›› 2020, Vol. 41 ›› Issue (1): 49-57.DOI: 10.13675/j.cnki. tjjs. 190343

第二代490N轨控发动机研制及在轨飞行验证

刘昌国^1,2,赵婷^1,2,姚锋^1,2,林庆国^1,2,梁军强³

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;3.北京控制工程研究所,北京;100190

出版日期:2020-01-20 发布日期:2020-01-20

Development and On-Orbit Flight Verification of the Second Generation 490N Liquid Apogee Engine

1.Shanghai Institute of Space Propulsion,Shanghai 201112,China;2.Shanghai Engineering Research Center of Space Engine,Shanghai 201112,China;3.Beijing Institute of Control Engineering,Beijing 100190,China

Online:2020-01-20 Published:2020-01-20

摘要/Abstract

摘要： 490N液体火箭发动机被广泛使用于航天器远地点机动入轨或者为其他轨道机动提供推力。我国第一代490N发动机真空比冲为304.7s，曾经成为制约我国航天器寿命上台阶的技术瓶颈，因此开展了基于铌合金材料的高性能第二代490N发动机研制工作，比冲提高10s。对第二代490N轨控发动机的研制和在轨飞行验证结果进行了总结和分析。第二代490N发动机研制过程中突破了高性能喷注器、耐高温材料及涂层、发动机头部喷注器法兰和燃烧室壁面结构温度控制、抗高量级力学环境能力以及热防护罩等多项关键技术，真空比冲达到了317.8s，单台发动机累计199次启动工作寿命40000s以上，工作性能达到国际同等水平。

关键词: 490N;轨控发动机;高性能;研制;飞行验证

Abstract: The 490N liquid apogee engines have been widely applied for the maneuvering into orbit of apogee spacecrafts or providing thrust of other orbital maneuvers. The vacuum specific impulse of the first generation 490N engine in China is 304.7s, which has become the technology bottleneck restricting the life of spacecraft in China. Therefore, the development of the second generation 490N engine with high performance based on niobium alloy materials has been carried out, and the aim of the specific impulse increased by 10s. The development of the second generation 490N orbit control engine and the results of on-orbit flight verification are summarized and analyzed. During the development of the second generation 490N engine, many key technologies include high performance injector, high temperature resistant material and coating, temperature control of head flange and wall structure of combustion chamber, high-level mechanical environment resistance and thermal shield. The vacuum specific impulse has reached up to 317.8s, the cumulative starting life of a single engine has reached up to more than 40000s and it had 199 start-ups, and the working performance has reached the international advanced level.

Key words: 490N;Liquid apogee engine;High performance;Development;Flight verification

刘昌国,赵婷,姚锋,林庆国,梁军强. 第二代490N轨控发动机研制及在轨飞行验证[J]. 推进技术, 2020, 41(1): 49-57.

LIU Chang-guo^1,2,ZHAO Ting^1,2,YAO Feng^1,2,LIN Qing-guo^1,2,LIANG Jun-qiang³. Development and On-Orbit Flight Verification of the Second Generation 490N Liquid Apogee Engine[J]. Journal of Propulsion Technology, 2020, 41(1): 49-57.

参考文献

[1] 林庆国. 空间轨控发动机高效燃烧室仿真与试验研究 [D]. 长沙:国防科技大学, 2015.
[2] Liu C G， Chen J， Han H Y， et al. A Long Duration and High Reliability Liquid Apogee Engine for Satellites[J]. Acta Astronautica， 2004， 55(3-9): 401-408.
[3] 赵婷，陈夏超，杨成虎，等. 面向高轨卫星的液体轨控发动机研制进展 [J]. 火箭推进， 2018， 44(1): 1-8.
[4] 杨成虎，林庆国，刘昌国. 高性能液体远地点发动机技术发展[J]. 火箭推进， 2013， 39(4): 1-7.
[5] Stechman C， Krismer D， Ueno F. Off-Limit Testing of the Model R-4D 110 LBF (490 N) Bipropellant Rocket Engine [R]. AIAA 2004-3694.
[6] Zidek R A， Kolmanovsky I V. Deterministic Drift Counteraction Optimal Control for Attitude Control of Spacecraft with Time-Varying Mass [R]. AIAA 2016-0369.
[7] Roibás-Millán E， Sorribes-Palmer F， Chimeno-Manguán M. The MEOW Lunar Project for Education and Science Based on Concurrent Engineering Approach[J]. Acta Astronautica， 2018， 148: 111-120.
[8] Zhang M Q， Liu C G. The Development and Flight History of the First Generation 490N Liquid Apogee Engine [R]. IAC-11-C4.1.15， 2011.
[9] Wu P K， Woll P， Stechman C， Fuller R， et al. Qualification Testing of a 2nd Generation High Performance Apogee Thruster [R]. AIAA 2001-3253.
[10] Schulte G. High Performance 400N MMH/NTO Bipropellant Engine for Apogee Boost Maneuvers[R]. AIAA 99-2466.
[11] Stechman C， Woll P， Fuller R， et al. A High Performance Liquid Rocket Engine for Satellite Main Propulsion [R]. AIAA 2000-3161.
[12] Henderson S， Stechman C， Wierenga K， et al. Performance Results for the Advanced Materials Bipropellant Rocket(AMBR) Engine[R]. AIAA 2010-6883.
[13] 刘昌国，姚锋，姜文龙，等. 一种提高双组元液体火箭发动机冷却液膜均匀性方法[P]. 中国国防发明专利: ZL
[14] 刘昌国，姚锋，姜文龙，等. 中小推力双组元姿轨控发动机边区液膜结构及其冷却方法[P]. 中国国防发明专利: ZL 201010052984.， 2014-10-22.
[15] Anderson W E， Yang V. Liquid Rocket Engine Combustion Instability [M]. Washington: American Institute of Aeronautics and Astronautics， 1995.
[16] 杨甫江，郭志辉，付虓. 基于热声网络法的燃烧不稳定性分析研究 [J]. 推进技术， 2014， 35(6): 822-829. ( YANG Fu-jiang， GUO Zhi-hui， FU Xiao. Analytic Study on Combustion Instability with a Thermoacoustic Network Model[J]. Journal of Propulsion Technology， 2014， 35(6): 822-829.)
[17] 汪广旭，郭灿琳，石晓波，等. 基于时滞模型的纵向燃烧不稳定性分析 [J]. 推进技术， 2016， 37(6): 1129-1135.
[18] Dighe S， Gadgil H. Effect of Transverse Acoustic Forcing on the Characteristics of Impinging Jet Atomization [J]. Atomization and Sprays， 2019， 29(1): 79-103.
[19] Flores W， Michelle O， Ahmed K A. Acoustic Mode Analysis of Rocket Thrust Chambers[R]. AIAA 2019-1579.
[20] Krismer D， Dorantes A， Miller S， et al. Qualification Testing of a High Performance Bipropellant Rocket Engine Using MON-3 and Hydrazine[R]. AIAA 2003-4775.
[21] 洪鑫，程惠尔，陈杰. 液体火箭发动机燃烧室声腔建模方法研究 [J]. 推进技术， 1999， 20(6): 19-22. (HONG Xin， CHENG Hui-er， CHEN Jie. Modeling Methods of Acoustic Cavity in Combustion Chamber of Liquid Rocket Engine[J]. Journal of Propulsion Technology， 1999， 20(6): 19-22.)
[22] Sutton G P， Biblarz O. Rocket Propulsion Elements [M]. USA: Wiley， 2016.
[23] Liu C G， Chen J. An Investigation on the Second Generation 490N Bipropellant Liquid Rocket Engine[C]. Beijing: International Symposium on Space Propulsion， 2007.
[24] 王迪，聂万胜，周思引，等. 单喷嘴模型发动机纵向高频燃烧不稳定性实验分析[J]. 实验流体力学， 2018， 32(2): 18-23.
[25] 张春基，吕宏军，贾中华，等. 铌钨合金材料在液体火箭发动机上的应用[J]. 宇航材料工艺， 2007， (6): 57-60.
[26] 徐方涛，张绪虎，贾中华. 姿/轨控液体火箭发动机推力室高温抗氧化涂层[J]. 宇航材料工艺， 2012， 42(1): 25-29.
[27] 周小军，赵刚，田进鹏. 一种面向航天器发动机的新型铌钨合金制备及其抗氧化涂层设计 [J]. 空间科学学报， 2016， 36(1): 99-105.
[28] 张忠利，张蒙正，周立新. 液体火箭发动机热防护[M]. 北京:国防工业出版社， 2016.
[29] Ono D， Dressler G， Kruse W， et al. The Design， Development， and Qualification of an Advanced Columbium Liquid Apogee Engine (AC-LAE) [R]. AIAA 98-3671.

第二代490N轨控发动机研制及在轨飞行验证

Development and On-Orbit Flight Verification of the Second Generation 490N Liquid Apogee Engine

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价