Citation: | Wang Xiaowei, Jin Ping, Cai Guobiaoet al. Method for investigation of combustion flowfield characteristics in single element gas/gas injector chamber[J]. Journal of Beijing University of Aeronautics and Astronautics, 2009, 35(9): 1095-1099. (in Chinese) |
[1] Davis J A, Campbell R L. Advantages of a full-flow staged combustion cycle engine system . AIAA 1997-3318,1997 [2] Moser M D, Pal S, Santoro R J, et al. laser light scattering measurements in a GO2/GH2 uni-element rocket chamber . AIAA 1995-0137,1995 [3] Foust M J, Deshpande M, Pal S, et al. Experimental and analytical characterization of a shear coaxial combustion GO2/GH2 flowfield . AIAA 1996-0646,1996 [4] Foust M J, Pal S, Santoro R J. Gaseous propellant rocket studies using raman spectroscopy . AIAA 1996-2766,1996 [5] Archambault M R, Talley D. Computational analysis of a single-element, shear-coaxial, GH2/GO2 engine . AIAA 2002-1088,2002 [6] Smith T D, Klem M D, Breisacher K J. Experimental evaluation of a subscale gaseous hydrogengaseous oxygen coaxial rocket injector . NASA/TM-2002-211982, 2002 [7] 庄逢辰.液体火箭发动机喷雾燃烧的理论、模型及应用[M].长沙:国防科技大学出版社, 1995 Zhuang Fengchen. Liquid rocket engine spray combustion: theory, modeling, and application[M]. Changsha: Press of National University of National Defense, 1995 (in Chinese) [8] 王福军.计算流体动力学分析[M].北京:清华大学出版社, 2004 Wang Fujun. Analysis of CFD [M]. Beijing: Tsinghua University Press, 2004 (in Chinese) [9] 赵坚行.燃烧的数值模拟[M].北京:科学出版社, 2002 Zhao Jianxing. The numerical simulation of combustion [M]. Beijing: Science Press, 2002(in Chinese)
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