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[1]王 勇,巨 乐,杨伟东,等.150 N气氧/煤油发动机涡流冷却技术试验[J].火箭推进,2020,46(03):26-32.
 WANG Yong,JU Le,YANG Weidong,et al.Experimental investigation on vortex-cooled technology of 150 N GO2/kerosene engine[J].Journal of Rocket Propulsion,2020,46(03):26-32.
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150 N气氧/煤油发动机涡流冷却技术试验

参考文献/References:

[1] 王爱玲, 林庆国, 吴建军. 运载火箭气氧/煤油姿控发动机技术研究[J]. 上海航天, 2006, 23(5): 6-11.
[2] 许宏博, 吉林, 金盛宇, 等. 气氧/煤油无毒姿控发动机技术研究[J]. 火箭推进, 2015, 41(5): 12-16.
XU H B, JI L, JIN S Y, et al. Technology of GOX/kerosene non-toxic attitude control engine[J]. Journal of Rocket Propulsion, 2015, 41(5): 12-16.
[3] CHIAVERINI M J, MALECKI M J, J ARTHUR S, et al. Vortex combustion chamber development for future liquid rocket engine applications[R]. AIAA 2002-4149.
[4] FANG D Q, MAJDALANI J, CHIAVERINI M J. Simulation of the cold-wall swirl driven combustion chamber[R]. AIAA 2003-5055.
[5] FANG D Q, MAJDALANI J, CHIAVERINI M J. Hot flow model of the vortex cold wall liquid rocket[R]. AIAA 2004-3676.
[6] JARTHUR S, KNUTH W H, MALECKI M J, et al. Development of a LOX/RP-1 vortex combustion cold-wall thrust chamber assembly[R].AIAA 2002-4144.
[7] CHIAVERINI M J, MALECKI M J, J ARTHUR S, et al. Vortex thrust chamber testing and analysis for O2-H2 propulsion applications[R]. AIAA 2003-4473.
[8] CHIAVERINI M J, J ARTHUR S, MUNSON S M. Laboratory characterization of vortex-cooled thrust chambers for methane/O2 and H2/O2[R]. AIAA 2005-4131.
[9] MARK A, RENE V, CRAIG R, et al. Vortex chamber flow field characterization for gelled propellant combustor applications[R]. AIAA 2003-4474.
[10] ROM C G, ANDERSON M H, CHIAVERINI M J. Cold flow analysis of a vortex chamber engine for gelled propellant combustor applications[R]. AIAA 2004-3359.
[11] MUNSON S M, J ARTHUR S, ROCHOLLJ D, et al. Development of a low-cost vortex-cooled thrust chamber using hybrid fabrication techniques[R]. AIAA 2011-5835.
[12] MAICKE B A, MAJDALANI J. Characterization of particle trajectories in the bidirectional vortex engine[R]. AIAA 2015-3849.
[13] MAJDALANI J, CHIAVERINI M J. Characterization of GO2-GH2 simulations of a miniature vortex combustion cold-wall chamber[J]. Journal of Propulsion and Power, 2017, 33(2): 387-397.
[14] 吴东波, 李家文, 常克宇. GH2/GO2涡流冷却推力室设计与数值计算[J]. 火箭推进, 2010, 36(5): 17-22.
WU D B, LI J W, CHANG K Y. Design and numerical calculation of GH2/GO2 vortex-cooled combustion chamber[J]. Journal of Rocket Propulsion, 2010, 36(5): 17-22.
[15] 唐飞, 李家文, 常克宇. 涡流冷却推力室中涡流结构的分析与优化[J]. 推进技术, 2010, 31(2): 165-169.
[16] 李家文, 唐飞, 俞南嘉. 推力室涡流冷却技术试验研究[J]. 推进技术, 2012, 33(6): 956-960.
[17] 李家文, 王化余, 叶汉玉, 等. 涡流冷却推力室燃烧效率分析[J]. 推进技术, 2013, 34(11): 1507-1512.
[18] 路强, 俞南嘉, 李恭楠, 等. GH2/GO2涡流冷却透明燃烧室方案设计及试验研究[J]. 火箭推进, 2013, 39(2): 1-5.
LU Q, YU N J, LI G N, et al. Design and experiment research of GH2/GO2 vortex-cooling transparent combustion chamber[J]. Journal of Rocket Propulsion, 2013, 39(2): 1-5.
[19] 李恭楠, 俞南嘉, 路强. 涡流冷却推力室流场特征与性能仿真[J]. 航空动力学报, 2014, 29(2): 420-426.
[20] YU N J, ZHAO B, LI G N, et al. Experimental and simulation study of a gaseous oxygen/gaseous hydrogen vortex cooling thrust chamber[J]. Acta Astronautica, 2016, 118: 11-20.
[21] 孙得川, 杨建文, 白荣博. 气氧/甲烷涡流冷壁燃烧室流场与壁面耦合传热分析[J]. 推进技术, 2011, 32(3): 401-406.

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备注/Memo

收稿日期:2019-09-27; 修回日期:2019-11-11
基金项目:国家自然科学基金(51606138)
作者简介:王勇(1987—),男,硕士,研究领域为喷雾与燃烧技术

更新日期/Last Update: 2020-06-25