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.
| 源语言 | 英语 |
|---|---|
| 页（从-至） | 414-418 |
| 页数 | 5 |
| 期刊 | Guti Huojian Jishu/Journal of Solid Rocket Technology |
| 卷 | 33 |
| 期 | 4 |
| 出版状态 | 已出版 - 8月 2010 |