Theoretical performance analysis of Mg/CO2 powdered rocket engine

被引：0
|
作者：
Li, Fang [1 ]
Hu, Chun-Bo [1 ]
He, Guo-Qiang [1 ]
机构：
[1] National Key Laboratory of Combustion, Flow and Thermo-Structure, College of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
来源：
Guti Huojian Jishu/Journal of Solid Rocket Technology | 2010年 / 33卷 / 04期
关键词：
Propulsion; -; Rockets;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
The theoretical performance of the powdered rocket engine is calculated theoretically in considering the specific impulse and the impact of factors. Compared with the traditional propulsion system, the powdered rocket engine has better specific impulse. In the calculation research of the performance of Mg and CO2, the rules of burning pressure, starting temperature and oxidizer-to-fuel ratio (by mass) were obtained.
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页码：414 / 418
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