|Table of Contents|

Analysis on the reusable cryogenic liquid rocket engine technology(PDF)

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

Issue:
2020年06期
Page:
1-12
Research Field:
专注与论述
Publishing date:

Info

Title:
Analysis on the reusable cryogenic liquid rocket engine technology
Author(s):
ZHANG Nan; SUN Huijuan
(Beijing Aerospace Propulsion Institute, Beijing 100076,China)
Keywords:
reusable technology;  reusable launch vehicle;  cryogenic liquid rocket engine;  guideline system;  propellant combination
PACS:
V434
DOI:
-
Abstract:
There has been increasing attention payed to the reusable launch vehicle, because it has the potential to reduce the cost of access to space.The rocket engine cost accounts for one-third of the cost of a rocket.The engine reusable performance is important for the reusable launch vehicle.Based on previous studies, present study analyzed the reusable technical developing trends in domestic and abord, and then suggest using the cryogenic liquid rocket engine as the propulsion of the reusable launch vehicle is a possible approach in the near future.This paper built the preliminary guideline system of reusable engines, and suggested the key technologies.

References:

[1] 马野,许健,邵秋虎.后航天飞机时代天地往返运载器发展趋势研究[J].中国航天,2015(3): 17-22.
[2] 于霞,孙伶俐,单文杰.国外可重复使用运载器发展现状和趋势[J].国际太空,2012(12): 2-6.
[3] BONHOMME C,IANNETTI A,GIRARD N,et al.Prometheus: European next generation liquid rocket engine [C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[4] RICHARDSON M P,HARDY D W F.Economic benefits of reusable launch vehicles for space debris removal [C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[5] 张明江,刘博.美国“猎鹰”-9火箭一子级重复使用影响分析[J].中国航天,2017(6): 18-20.
[6] GRANTZ A C.X-37B orbital test vehicle and derivatives[R].AIAA 2011-7315.
[7] BOND A,VARVILL R.The SKYLON spaceplane[C]//the Institution of Electrical Engineers.Savoy Place,London: IEE,1999.
[8] 牛文,李文杰.SKYLON飞行器与SABRE发动机研究[J].飞航导弹,2013(3): 70-75.
[9] KNOCHE R,MEYER M,RAKERS S.The national proceed programme-Innovative launcher technologies to enhance cryogenic upper stages [C]//69th International Astronautical Congress.Bremen,Germany: the International Astronautical Federation,2018.
[10] GSTATTENBAUER G,FRANKE M,LIVINGSTON J.Cost comparison of expendable,hybrid,and reusable launch vehicles[C]//Space 2006.San Jose,California.Reston,Virigina: AIAA,2006.
[11] ZHANG H W,GUO J,XU Y S,et al. Research on TSTO reusable launch vehicle powered by turbo-aided RBCC engine[R]. AIAA 2017-2372.
[12] MARC L W.RL 10A-5: an assessment of reusability demonstrated during the SSRT program[R].AIAA 1996-3110.
[13] 毕海亮.国外新型运载火箭型号研制进度概览[J].中国航天,2018(11): 48-53.
[14] DOWNER B,WELCH C,SWINNEY R W.Innovation and investment strategies of commercial sector reusable launch vehicles.[C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[15] HELLMAN B M,BRADFORD J E,ST GERMAIN B D,et al.Two stage to orbit conceptual vehicle designs using the SABRE engine[C]//AIAA SPACE 2016.Long Beach,California.Reston,Virginia: AIAA,2016.
[16] MEHTA U B,AFTOSMIS M J,BOWLES J V,et al. Skylon aerodynamics and SABRE plumes[C]//20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston,Virginia: AIAA.
[17] 杨开,才满瑞.国外液氧/甲烷发动机的最新进展[J].中国航天,2017(10): 14-19.
[18] NONAKE S,ITO T,INANANI Y.Technology demonstration and system design for reusable rocket flight experiment[C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[19] AOKI K,OBASE K,MOCHIZUKI K,et al.Development plan and demonstration of Japanese reusable launch vehicle[C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[20] KIMURA T,HASHIMOTO T,SATO M,et al.Development of a reusable LOX/LH2 rocket engine-firing tests and lifetime evaluation analysis[C]//51st AIAA/SAE/ASEE Joint Propulsion Conference.Virginia: AIAA,2015.
[21] GABRIELLI A,CRAMAROSSA A,DAVERSA E,et al.Italian contribution to the ESA ministerial conference 2016: next generation of the European Vega launcher for new green and reusable space missions[C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[22] GILIES D.Rocket lab: opening access to leo for the small satellite market[C]//69th International Astronautical Congress.Bremen,Germany: the International Astronautical Federation,2018.
[23] HAGEMANN G,PRECLIK D,BRUMMER L,et al.TEKAN 2010-thrust chamber technologies for liquid rocket propulsion[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Sacramento,California.Reston,Virigina: AIAA,2006.
[24] BUSSLER L,SIPPEL M.Comparison of return options for reusable first stages[R].AIAA 2017-2137.
[25] 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.Liquid rocket engines working on LOX/methane for space transportation systems of the 21 century [J].Journal of Rocket Propulsion,2002,28(1): 50-54.
[26] 张贵田.高压补燃液氧煤油发动机[M].北京: 国防工业出版社,2005: 502.
[27] 尹亮,刘伟强.液氧/甲烷发动机研究进展与技术展望[J].航空兵器,2018(4): 21-27.
[28] 潘亮,刘倩. 国内外液氧/甲烷液体火箭发动机近期研制进展[C]//第二届空天动力联合会议论文集. 大连:中国航天第三专业信息网,2017.
[29] ROBINSON J W,RHODES R E.Next generation reusable space transportation system[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference.Atlanta,GA.Reston,Virginia: AIAA,2017.
[30] FANG X X,SHEN C B.Study on atomization and combustion characteristics of LOX/methane pintle injectors[J].Acta Astronautica,2017,136: 369-379.
[31] PRECLIK D,HAGEMANN G,KNAB O,et al.LOX/hydrocarbon propellant trade considerations for future reusable liquid booster engines[C]//41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Tucson,Arizona.Reston,Virigina: AIAA,2005.
[32] 王海燕,高玉闪,邢理想.全流量补燃循环液氧甲烷发动机系统方案研究[J].载人航天,2019,25(2): 236-242.
[33] 李文龙,李平,邹宇.烃类推进剂航天动力技术进展与展望未来[J].宇航学报,2015,36(3): 243-252.
[34] 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.
[35] 曹红娟,赵海龙,蔡震宇,等.登月下降级液氧甲烷发动机方案研究[J].载人航天,2016,22(2): 186-190.
[36] 黄仕启,刘登丰,崔荣军.液氧/甲烷膨胀循环发动机研究[J].导弹与航天运载技术,2015(6): 25-28.
[37] 张思远,孙慧娟,周利民.变推力液氧/甲烷膨胀循环发动机系统方案研究[J].导弹与航天运载技术,2015(4): 16-19.
[38] 刘士杰,梁国柱.航天飞机主发动机高压燃料涡轮泵的故障模式[J].航空动力学报,2015,30(3): 611-626.
[39] JIN P,XU J B,WANG J,et al.Numerical simulation of influence of injector parameters on combustion in LOX/Methane engine[C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[40] CHENG C,WANG Y B,LIU Y,et al.Numerical investigation of low cycle fatigue life for channel wall nozzles[J].Journal of Aerospace Power,2018,33(7): 1553-1565.
[41] ANFIMOV N.The principle directions of Russian activities in research for conception of future reusable space transportation system-The program ‘Oryol'(Eagle)[C]//International Aerospace Planes and Hypersonics Technologies.Chattanooga,TN,USA.Reston,Virigina: AIAA,1995.
[42] DUMONT E,STAPPERT S,ECKER T,et al.Evaluation of future Ariane reusable VTOL booster stages[C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[43] MADDOCK C A,RICCIARDI L,WEST M,et al.Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites[J].Acta Astronautica,2018,152: 782-792.
[44] BOUE Y,VINET P,MAGNIANT S,et al.LOX/methane reusable rocket propulsion at reach with large scale demonstrators tested[J].Acta Astronautica,2018,152: 542-556.
[45] SONG J W,SUN B.Thermal-structural analysis of regeneratively-cooled thrust chamber wall in reusable LOX/Methane rocket engines[J].Chinese Journal of Aeronautics,2017,30(3): 1043-1053.
[46] RICHARDSON M P.A novel approach to cooling and service life extension in reusable rocket engine thrust chambers[C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[47] 禹天福,李亚裕.液氧/甲烷发动机的应用前景[J].航天制造技术,2007(2): 1-4.
[48] 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,ZHANG 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.
[49] 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(4): 14-20. ZHANG X P,LI C H,MA D Y.Study on the LOX/methane rocket engine power cycles[J].Journal of Rocket Propulsion,2009,35(4): 14-20.
[50] 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(3): 21-26. MA D Y,LU G,ZHANG X P,et al.Research on hot tests of LOX/methane gas generator[J].Journal of Rocket Propulsion,2013,39(3): 21-26.
[51] KLMYKOV G P,MOSSOLOV S V.Liquid rocket engines working on oxygen + methane for space transportation systems of the XXI century(on the results of scientific and experimentalstudies[C]//51st International Astronautical Congress.Rio de Janeiro,Brazil: the American Institute of Aeronautics and Astronautics,2000.
[52] THOMPSON R C,THOMAS D,FARRINGTON P.A framework for assessing the reusability of hardware(reusable rocket engines)[R].NASA/CR-M17-5695,2016.
[53] SAMPSON M.The next frontier: innovative launch services[C]//68th International Astronautical Congress.Adelaide,Australia: the International Astronautical Federation,2017.
[54] MAJUMDAR A K,LECLAIR A,HEDAYAT A.Numerical modeling of pressurization of cryogenic propellant tank for integrated vehicle fluid system[C]//52nd AIAA/SAE/ASEE Joint Propulsion Conference.Salt Lake City,UT.Reston,Virginia: AIAA,2016.
[55] CHA J,HA C,KO S,et al.Application of fault factor method to fault detection and diagnosis for space shuttle main engine[J].Acta Astronautica,2016,126: 517-527.

Memo

Memo:
-
Last Update: 1900-01-01