| 铝镁贫氧推进剂低压可燃极限研究 |
| |
| 引用本文： | 张炜,朱慧,薛金根,方丁酉,夏智勋,姜春林,万章吉.铝镁贫氧推进剂低压可燃极限研究[J].推进技术,1999,20(2):95-98. |
| |
| 作者姓名： | 张炜 朱慧 薛金根 方丁酉 夏智勋 姜春林 万章吉 |
| |
| 作者单位： | 国防科技大学材料科学与应用化学系,长沙,410073 |
| |
| 摘 要： | 采用推进剂静态燃速测试和非壅塞式固体火箭冲压发动机实验的方法，研究了铝镁贫氧推进剂配方对其低压可燃极限的影响。研究表明，增加氧化剂的含量、添加燃速催化剂和采用超细金属添加剂，可以拓宽铝镁贫氧推进剂的低压可燃极限，满足非壅塞式固体火箭冲压发动机的基本要求。
|
| 关 键 词： | 固体燃料冲压发动机，贫氧富燃料推进剂，推进剂燃烧，低压燃烧，可燃极限 |
| 修稿时间： | 1998-04-24 |
FLAMMABILITY LIMITS OF ALUMINUM MAGNESIUM FUEL RICH PROPELLANT |
| |
| Zhang Wei,Zhu Hui,Xue Jingen,Fang Dingyou,Xia Zhixun,Jiang Chunlin and Wan Zhangji.FLAMMABILITY LIMITS OF ALUMINUM MAGNESIUM FUEL RICH PROPELLANT[J].Journal of Propulsion Technology,1999,20(2):95-98. |
| |
| Authors: | Zhang Wei Zhu Hui Xue Jingen Fang Dingyou Xia Zhixun Jiang Chunlin and Wan Zhangji |
| |
| Institution: | Dept.of Material Science and Applied Chemistry,National Univ. of Defence Technology,Changsha,410073;Dept.of Material Science and Applied Chemistry,National Univ. of Defence Technology,Changsha,410073;Dept.of Material Science and Applied Chemistry,National Univ. of Defence Technology,Changsha,410073;Dept.of Material Science and Applied Chemistry,National Univ. of Defence Technology,Changsha,410073;Dept.of Material Science and Applied Chemistry,National Univ. of Defence Technology,Changsha,410073;Dept.of Material Science and Applied Chemistry,National Univ. of Defence Technology,Changsha,410073;Dept.of Material Science and Applied Chemistry,National Univ. of Defence Technology,Changsha,410073 |
| |
| Abstract: | The effect of the composition of aluminum
magnesium fuel rich propellant on the flammability limit was studied by means of the burning
rate measurement and the direct connected pipe test of an unchoked solid ramrocket.The
methods to broaden the flammability limit of the fuel rich propellant were investigated.The
results show that sustained combustion at low pressure and high burning rate can be improved
when increasing the oxidizer content and adding burning rate modifiers or the super fine
aluminum powder.The improved fuel rich propellant can be used in the unchoked solid
ramrocket |
| |
| Keywords: | Solid fueled ramjet Oxygen poor fuel rech propellant Propellant combustion Low pressure combustion Flammability limit |
| 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 |
|
