航天推进技术研究院主办
SHI Chao.Review of ramjet ground-test facilities and relevant technology development[J].Journal of Rocket Propulsion,2021,47(01):1-12.
冲压发动机地面试验技术及试验能力述评
- Title:
- Review of ramjet ground-test facilities and relevant technology development
- 文章编号:
- 1672-9374(2021)01-0001-12
- Keywords:
- ramjet engine; ground-test; test technology; test facility capacity
- 分类号:
- V433.9
- 文献标志码:
- A
- 摘要:
- 分析了试验气体加热技术、变马赫数试验技术以及光学测量技术等冲压发动机地面试验关键技术的发展趋势,梳理了美国、俄罗斯、日本、法国以及中国等国家的主要冲压发动机地面试验设施运营管理机构,并对典型试验设施的能力进行了介绍。通过梳理分析国外冲压发动机地面试验技术发展趋势和试验能力现状,指出了我国冲压发动机地面试验能力和技术与国外存在的差距,对我国冲压发动机地面试验能力建设和技术发展方向提出了建议。
- Abstract:
- In this work, the development trend of ramjet ground-test technologies, such as tested gas heating, varying Mach number and optical measuring techniques were analyzed. The capacities and its operation and manager institutes of some typical facilities in USA, Russia, Japan, France and China were combed systematically. Based on the analysis of the abroad ground-test facility capacities and relevant technology development trend, we pointed out the gap between our country with other developed countries, and proposed some suggestions on the test capacity promotion and technology development.
参考文献/References:
[1] 胡冬冬,牛文,李文杰,等.美国高超声速地面试验设施建设现状及能力提升举措分析[J].飞航导弹,2015(3):3-9.
[2] 胡冬冬,牛文,陈英硕,等.美国高超声速技术试验设施建设历史教训及启示[J].飞航导弹,2015(2):9-12.
[3] 钟萍,陈丽艳,王颖.国外高超声速技术焦点领域及相关设备改造综述[J].飞航导弹,2011(10):17-22.
[4] LESLIE J,MARREN D.Hypersonic test capabilities overview[C]//U.S.Air Force T&E Days 2009.Reston,Virigina: AIAA,2009.
[5] 赵芳.低总温直连式空气加热器数值仿真与试验研究[D].长沙: 国防科学技术大学,2012.
[6] 罗飞腾.污染空气对煤油燃料超燃冲压发动机性能的影响研究[D].西安: 西北工业大学,2012.
[7] SERRE L.ONERA potential for scramjet ground testing up to Mach 12[C]//AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference.Capua,Italy.Reston,Virigina: AIAA,2005.
[8] THOMAS S,LEE J,STEPHENS J,et al.The mothball,sustainment,and proposed reactivation of the hypersonic tunnel facility(HTF)at NASA Glenn research center plum brook station[C]//27th AIAA Aerodynamic Measurement Technology and Ground Testing Conference.Reston,Virigina: AIAA,2010.
[9] GOYNE C,CRESCI D.Hy—V program overview and status[C]//15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Reston,Virigina: AIAA,2008.
[10] TOMIOKA S,HIRAIWA T,KOBAYASHI K,et al.Vitiation effects on scramjet engine performance in Mach 6 flight conditions[J].Journal of Propulsion and Power,2007,23(4):789-796.
[11] SERRE L,FALEMPIN F.Development of S4 free jet test facility for the French LEA flight test program[C]//15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Dayton,Ohio.Reston,Virigina: AIAA,2008.
[12] SAARI D,CHU P,JAUCH C.Clean air regenerative storage heater technology for propulsion test facilities[C]//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference.Bremen,Germany.Reston,Virigina: AIAA.
[13] FANK K L,MARREN D E.先进高超声速试验设备[M].黄训铭,译.北京: 航空工业出版社,2015.
[14] 冯军红.高焓高压空气加热器数值仿真与试验研究[D].长沙: 国防科学技术大学,2011.
[15] DROZDA T G,CABELL K F,ZILTZ A R,et al.Comparisons between NO PLIF imaging and CFD simulations of mixing flowfields for high—speed fuel injectors[C]//53rd AIAA/SAE/ASEE Joint Propulsion Conference.Atlanta,GA.Reston,Virginia: AIAA,2017.
[16] SMITH D M,YOUNKER T.Comparative ablation testing of carbon phenolic TPS materials in the AEDC—H1arcjet[C]//AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference.Capua,Italy.Reston,Virigina: AIAA,2005.
[17] VIGUIER P,GARRAUD J,SOUTADE J,et al.Scramjet tests in the ONERA F4 hotshot wind tunnel[C]//19th AIAA International Space Planes and Hypersonic Systems and Technologies Conference.Atlanta,GA.Reston,Virginia: AIAA,2014.
[18] 胡冬冬,叶蕾.从高速系统试验(HSST)项目看美国高超声速试验科学技术专项实施现状[J].飞航导弹,2016(4):22-27.
[19] 钟萍.国外高超声速飞行加速地面模拟能力研究进展[J].飞航导弹,2014(6):10-15.
[20] GARRARD D,SEELY J,ABEL L.An analysis of alternatives to provide a varying Mach number test capability at APTU[C]//14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference.Canberra,Australia.Reston,Virigina: AIAA,2006.
[21] MONTGOMERY P,GARRARD D.Test and evaluation of hypersonic aeropropulsion systems along flight trajectories in a time—varying flight environment[C]//41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Tucson,Arizona.Reston,Virigina: AIAA,2005.
[22] 黄斌.基于TDLAS的RBCC发动机出口燃烧流场诊断实验研究[D].西安: 西北工业大学,2015.
[23] 叶景峰.超燃冲压发动机燃烧流场羟基分子标记速度测量技术研究[D].西安: 西北工业大学,2019.
[24] KOHSE-HOINGHAVS K, JEFFRIES J B.应用燃烧诊断学[M].刘晶儒,叶景峰,陶波,等译.北京:国防工业出版社,2017.
[25] 王璐,韩洪涛,王友利.2017年国外高超声速技术发展回顾[J].国际太空,2018(3):41-45.
[26] 张灿,林旭斌,胡冬冬,等.2018年国外高超声速飞行器技术发展综述[J].飞航导弹,2019(2):1-5.
[27] 胡冬冬,刘晓明,张绍芳,等.2016年国外高超声速飞行器技术发展综述[J].战术导弹技术,2017(1):28-33.
[28] 李文杰,牛文,叶蕾.美国准备地面试验10倍于X—51A的超燃冲压发动机[J].飞航导弹,2015(3):10-13.
[29] 田宏亮.临近空间高超声速武器发展趋势[J].航空科学技术,2018,29(6):1-6.
[30] GARRARD D.Hypersonic test capabilities at the aerodynamic and propulsion test unit [R].AIAA 2015-1784.
[31] 龚红明.0.6米激波风洞马赫数8喷管设计及数值计算[D].重庆: 重庆大学,2015.
[32] 栗继伟.JFX爆轰驱动激波风洞关键问题研究[D].太原: 中北大学,2017.
[33] 吕治国,李国君,赵荣娟,等.卡尔斯潘公司高超声速脉冲设备建设历程分析[J].实验流体力学,2014,28(5):1-6.
[34] 杨阳.污染组分对超燃冲压发动机性能的影响研究[D].成都: 西南交通大学,2009.
[35] CURRAN E T,MURTHY S N B.Scramjet propulsion [C]//Progress in Astronautics and Aeronautics.Washington,DC: AIAA,2001.
[36] MCCLINTON C,ROUDAKOV A,SEMENOV V,et al.Comparative flow path analysis and design assessment of an axisymmetric hydrogen fueled scramjet flight test engine at a Mach number of 6.5[C]//Space Plane and Hypersonic Systems and Technology Conference.Norfolk,VA,USA.Reston,Virigina: AIAA,1996.
[37] VOLAND R,AUSLENDER A,SMART M,et al.CIAM/NASA Mach 6.5 scramjet flight and ground test[C]//9th International Space Planes and Hypersonic Systems and Technologies Conference.Norfolk,VA,USA.Reston,Virigina: AIAA,1999.
[38] 茆青.高超声速风洞带式电阻加热器强化换热数值研究[D].绵阳: 中国空气动力研究与发展中心,2016.
[39] ORTH R,KISLYKH V.American/Russian hypersonic combustion research experiments in the TSNIIMASH PGU—11 facility[C]//33rd Aerospace Sciences Meeting and Exhibit.Reno,NV,USA.Reston,Virigina: AIAA,1995.
[40] 赵小运.板片蓄热式加热器设计方法研究[D].长沙: 国防科学技术大学,2011.
[41] CHEVALIER A,FALEMPIN F.Review of new French facilities for PREPHA program[C]//International Aerospace Planes and Hypersonics Technologies.Chattanooga,TN,USA.Reston,Virigina: AIAA,1995.
[42] HOHN O M.Experimental investigation of sidewall compression and internal contraction in a scramjet inlet[J].Journal of Propulsion and Power,2017,33(2):501-513.
[43] FALEMPIN F,SERRE L.French contribution to hypersonic airbreathing propulsion technology development—status in 2006[C]//42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.Sacramento,California.Reston,Virigina: AIAA,2006.
[44] OLIVIER H,HABERMANN M,BLEILEBENS M.Use of shock tunnels for hypersonic propulsion testing[C]//35th Joint Propulsion Conference and Exhibit.Los Angeles,CA,USA.Reston,Virigina: AIAA,1999.
[45] SCHRAMM J M,SUNAMI T,et al.Experimental investigation of supersonic combustion in the HIEST and HEG free piston driven shock tunnels[R].AIAA 2010-7122.
[46] 俞鸿儒.大幅度延长激波风洞试验时间[J].中国科学: 物理学 力学 天文学,2015,45(9):6-11.
[47] 王振锋.脉冲设备二维高超进气道压缩面激波—边界层干扰显示技术及应用研究[D].绵阳: 中国空气动力研究与发展中心,2015.
[48] 陈苏宇.高超声速压缩拐角气动热环境研究[D].绵阳: 中国空气动力研究与发展中心,2014.
[49] 乐嘉陵.吸气式高超声速技术研究进展[J].推进技术,2010,31(6):641-649.
[50] 谭宇,毛雄兵,焦伟,等.燃烧风洞不同模拟方式对超燃发动机性能影响试验研究[J].推进技术,2017,38(9):2062-2068.
[51] 邓维鑫.宽范围马赫数超燃冲压发动机燃烧组织技术研究[D].成都: 西南交通大学,2013.
[52] 钟战.超声速气流中气化煤油的喷注与燃烧特性研究[D].长沙: 国防科学技术大学,2015.
[53] 吕仲.固体火箭超燃冲压发动机工作特性研究[D].长沙: 国防科学技术大学,2012.
[54] 李庆.基于凹腔火焰稳定器的亚燃冲压发动机燃烧室点火过程研究[D].长沙: 国防科学技术大学,2010.
[55] 吴海燕.超燃冲压发动机燃烧室两相流混合燃烧过程仿真及实验研究[D].长沙: 国防科学技术大学,2009.
[56] 陈植.超燃冲压发动机隔离段流动机理及其控制的试验研究[D].长沙: 国防科学技术大学,2015.
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备注/Memo
收稿日期:2020-07-15
作者简介:史超(1967—),男,研究员,研究领域为液体火箭发动机试验技术。