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�������պ����ѧѧ�� 2011, Vol. 37 Issue (4) :384-389    DOI:
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Modeling of hydrogen engine parameters design during flight to orbit of reusable launch vehicle
Jin Ping, Wang Xiaowei, Li Mao, Cai Guobiao*
School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

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Abstract�� In order to investigate the influence of hydrogen engine parameters on launch vehicle performance, the mathematical models suited for single stage to orbit reusable launch vehicle flight process were brought up based on hydrogen engine performance parameters, including rocket motion equations, flight control conditions and vehicle mass model. The vehicle mass variety rules were discussed in detail changed with hydrogen engine mixture ratio during flight to orbit. The results show that on the condition the vehicle gross mass set, when hydrogen engine mixture ratio increases from 4 to 14, propellants mass and engine mass decrease firstly and then increase, tank mass decrease all the time, which synthetically bring forth payload mass increase firstly and then decrease.
Keywords�� reusable launch vehicle   flight parameters   payload mass   hydrogen engine   mixture ratio     
Received 2010-01-19;
About author: �� ƽ(1979-),Ů,���������,��ʿ��,jinping@buaa.edu.cn.
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��ƽ, ��С��, ��ï, �̹��.����RLV���й��̵������������������ģ��[J]  �������պ����ѧѧ��, 2011,V37(4): 384-389
Jin Ping, Wang Xiaowei, Li Mao, Cai Guobiao .Modeling of hydrogen engine parameters design during flight to orbit of reusable launch vehicle[J]  JOURNAL OF BEIJING UNIVERSITY OF AERONAUTICS AND A, 2011,V37(4): 384-389
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http://bhxb.buaa.edu.cn//CN/     ��     http://bhxb.buaa.edu.cn//CN/Y2011/V37/I4/384
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