| [1] Roux A, Gicquel L Y M, Reichstadt S, et al. Analysis of unsteady reacting flows and impact of chemistry description in large eddy simulations of side-dump ramjet combustors[J]. Combustion and Flame, 2010(157): 176-191.[2] Handa T, Miyachi H, Kakuno H, et al. Generation and propagation of pressure waves in supersonic deep cavity flows[J]. Experiments in Fluids, 2012, 3(6): 1855-1866.[3] Liu X Z. Power pack of cruise missile[M]. Beijing: China Astronautic Publishing House, 2005 (in Chinese). 刘兴洲.飞航导弹动力装置[M]. 北京: 中国宇航出版社, 2005.[4] Fry R S. A century ramjet propulsion technology evolution[J]. Journal of Propulsion and Power, 2004, 20(1): 27-58.[5] Yu G,Fan X J. Supersonic combustion and hypersonic propulsion[J]. Advances in Mechanics, 2013, 43(5): 449-471 (in Chinese). 俞刚, 范学军. 超声速燃烧与高超声速推进[J].力学进展, 2013, 43(5): 449-471.[6] Zetterstrom K A, Sjoblom B. An experimental study of side dump ramjet combustors, ISABE-85-7024[R]. Cincinnati: ISABE, 1985.[7] Stull F D, Craig R R, Streby G D, et al. Investigation of a dual inlet side dump combustor using liquid duel injecti-on, AIAA-1983-0420[R]. Reston: AIAA, 1983.[8] Alard P. Fuel injection system for ramjet engine: USA,U.S. P, 4852348 [P]. 1988.[9] Qiu X Y, Gong B Q. An experimental investigation on the combustor with bypass flom in integral liquid fuel ramjet[J]. Journal of Propulsion Technology, 1992(5): 18-24(in Chinese). 邱新宇, 宫本泉. 整体式液体冲压发动机分流方案燃烧室试验研究[J]. 推进技术, 1992(5): 18-24.[10] Chen J M. Numerical simulation of dump combustion chamber of side inlet ramjet[D]. Beijing: Beijing Power Machinery Institute, 2007 (in Chinese). 陈静敏. 旁侧进气冲压发动机突扩燃烧室流场数值模拟[D]. 北京: 北京动力机械研究所, 2007.[11] Chen J M, Li Z Y, Wang D Y, et al. Combustion performace study of side dump heater[J]. Journal of Propulsion Technology, 2013, 34(12): 1677-1681 (in Chinese). 陈静敏, 李志永, 王登云, 等. 旁侧突扩加热器燃烧性能研究[J].推进技术, 2013, 34(12): 1677-1681.[12] Laruelle G. Synthesis of aerodynamic studies of air intake of a highly manoeuvring missile athigh mach numbers, ISABE-85-7011[R]. Cincinnati: ISABE, 1985.[13] Wang F J. Computational fluid dynamics analysis: the principle and application of CFD software[M]. Beijing: Tsinghua University Press, 2001 (in Chinese). 王福军. 计算流体动力学分析-CFD软件原理与应用[M]. 北京: 清华大学出版社, 2001.[14] Jin Z G, Zhang K Y. Concept of a two-dimensional supersonic/hypersonic inlet with a non-conventional compression wall[J]. Journal of Propulsion Technology, 2004, 25(3): 226-229 (in Chinese). 金志光, 张堃元. 二维非常规压缩型面超/高超声速进气道的设计概念[J]. 推进技术, 2004, 25(3): 226-229.[15] Emery J C, Sterett J R. Experimental separation studies for two-dimensional wedges and curved surfaces at mach numbers of 4.8 to 6.2, NASA TN D-1014[R]. Washington, D.C.: NASA, 1962.[16] Jin Z G, Zhang K Y. A variable geometry scramjet inlet with a translating cowl operating in a large mach number range[J]. Journal of Astronautics, 2010, 31(5): 1503-1510 (in Chinese). 金志光, 张堃元. 宽马赫数范围高超声速进气道伸缩唇口式变几何方案[J]. 宇航学报, 2010, 31(5): 1503-1510.[17] Ju Y. Design of curved shock compression surface and experimental investigation[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2005 (in Chinese). 居燕. 弯曲激波压缩面设计及试验研究[D]. 南京: 南京航空航天大学, 2005.[18] Wang X J. Spacecraft enter and return (Part II)[M]. Beijing: China Aerospace Press, 1991 (in Chinese). 王希季. 航天器进入与返回技术(下册)[M]. 北京: 宇航出版社, 1991. |
CJA
