Modeling of hydrogen engine parameters design during flight to orbit of reusable launch vehicle

[1] Sutton G,Binlarz O.火箭发动机基础[M].7版.洪鑫,张宝炯译.北京:科学出版社,2001:75-83 Sutton G,Binlarz O.Rocket propulsion elements[M].Seventh ed.Translated by Hong Xin,Zhang Baojiong.Beijing:Science Press,2001:75-83(in Chinese) [2] 谭建国,徐万武,王振国.氢氧发动机实现单级入轨的优化分析[J].上海航天,2003(2):5-7 Tan Jianhuo,Xu Wanwu,Wang Zhenguo.Optimal analysis of hydrogen-oxygen engine for SSTO[J].Shanghai Astronautics,2003(2):5-7(in Chinese) [3] Stanley D,Talay T,Lepsch R.Conceptual design of a fully reusable manned launch system[J].Journal of Spacecraft and Rockets,1992,29(4):529-537 [4] 朱森元.氢氧火箭发动机及其低温技术[M].北京:国防工业出版社,1995:66-73 Zhu Senyuan.Hydrogen/oxygen engine and cryogenics technology[M].Beijing:National Defense Industry Press,1995:66-73 (in Chinese) [5] Martin J,Manski D.Variable-mixture-ratio and other rocket engines for advanced shuttles[J].Journal of Propulsion and Power,1991,7(4):549-555 [6] 黄卫东,王克昌,陈启智.液体火箭发动机对单级入轨运载器的影响[J].推进技术,1997,18(6):19-22 Huang Weidong,Wang Kechang,Chen Qizhi.Effect of liquid rocket engine on the single-stage-to-orbit vehicle[J].Journal of Propulsion,1997,18(6):19-22 (in Chinese) [7] 黄奕勇,张育林.变混合比及三组元发动机用于单级入轨[J].推进技术,1998,19(5):1-5 Huang Yiyong,Zhang Yulin.Variable mixture-ratio and tripropellant rocket for SSTO[J].Journal of Propulsion,1998,19(5):1-5(in Chinese) [8] Colasurdo G,Pastrone D,Casalino L.Mixture-ratio control to improve hydrogen-fuel rocket performance[J].Journal of Spacecraft and Rockets,1997,34(2):214-217 [9] 肖业伦.航空航天器运动的建模——飞行动力学的理论基础[M].北京:北京航空航天大学出版社,2003:23-25 Xiao Yelun.Modeling of aircraft and spacecraft motion—flight dynamics elements[M].Beijing:Beijing University of Aeronautics and Astronautics Press,2003:23-25(in Chinese) [10] Davis J,Campbell R.Advantages of a full-flow staged combustion cycle engine system .AIAA 97-3318,1997 [11] Johnson T,Waters W.Thermal-structural optimization of integrated cryogenic propellant tank concepts for a reusable launch vehicle .AIAA 2004-1931,2004