| 固液火箭发动机装药设计优化 |
| |
| 引用本文： | 曹泰岳,师艳辉,吴海波.固液火箭发动机装药设计优化[J].推进技术,2000,21(1):67-70. |
| |
| 作者姓名： | 曹泰岳 师艳辉 吴海波 |
| |
| 作者单位： | 国防科技大学航天技术系,湖南,长沙,410073 |
| |
| 摘 要： | 按两类不同的气化速率公式，讨论了固液火箭发动机燃料装药优化设计的方法和程序，并针对某ＨＴＰＢ／ＬＰＸ（或ＧＯＸ）发动机，给出了多孔装药在不同孔数的情形下某些参数随时间的变化以及另一些参数的总体值或平均值，最后应燃料装药设计和配方设计给出了某些结论。
|
| 关 键 词： | 推进剂药柱 配方 最优设计 固液火箭发动机 |
Optimization of grain design for hybrid rocket engine |
| |
| Cao Taiyue,Shi Yanhui and Wu Haibo.Optimization of grain design for hybrid rocket engine[J].Journal of Propulsion Technology,2000,21(1):67-70. |
| |
| Authors: | Cao Taiyue Shi Yanhui and Wu Haibo |
| |
| Institution: | Dept of Aerospace Technology ,National Univ of Defence Technology ,Changsha 410073,China;Dept of Aerospace Technology ,National Univ of Defence Technology ,Changsha 410073,China;Dept of Aerospace Technology ,National Univ of Defence Technology ,Changsha 410073,China |
| |
| Abstract: | The method and the procedure of design optimization for fuel grain of hybrid rocket engines were discussed using two different kinds of formula for fuel regression rate With multi port grain of some HTPB/LOX(or GOX) engine the variation of some parameters with time and other parameters were given for different numbers of port Some conclusions were drawn on fuel grain design and fuel ingredient design |
| |
| Keywords: | Hybrid propellant rocket engines propellant grain Propellant formulation Optimization design |
| 本文献已被 CNKI 维普 万方数据 等数据库收录！ |
| 点击此处可从《推进技术》浏览原始摘要信息 |
| 点击此处可从《推进技术》下载免费的PDF全文 |
|
