| 引用本文: | 钟涛,张为华,王中伟.大长径比固体火箭发动机点火瞬态过程数值分析.[J].国防科技大学学报,2004,26(6):5-8.[点击复制] |
| ZHONG Tao,ZHANG Weihua,WANG Zhongwei.Numerical Study of Ignition Transient in Large Aspect Ratio Solid Rocket Motor[J].Journal of National University of Defense Technology,2004,26(6):5-8[点击复制] |
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| 大长径比固体火箭发动机点火瞬态过程数值分析 |
| 钟涛, 张为华, 王中伟 |
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(国防科技大学 航天与材料工程学院，湖南 长沙 410073)
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| 摘要: |
| 研究大长径比固体火箭发动机点火瞬态特性，采用守恒型N-S方程描述了集点火器、燃烧室和喷管于一体的数学仿真模型，应用NND－3差分格式进行数值求解，计算结果表明，点火期间，发动机内除了压强急升之外，还存在振荡和拍击现象。 |
| 关键词: 大长径比固体火箭发动机 点火瞬态过程 一体化模型 |
| DOI： |
| 投稿日期：2004-06-29 |
| 基金项目:国家863高技术项目资助(2002AA765030) |
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| Numerical Study of Ignition Transient in Large Aspect Ratio Solid Rocket Motor |
| ZHONG Tao, ZHANG Weihua, WANG Zhongwei |
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(College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China)
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| Abstract: |
| Using N-S equations to describe the ignition transient model of the large aspect ratio solid rocket motor, this model includes the igniter and burning room and nozzle. Comparing the calculation and experiment shows the correction of it. Furthermore, there are vibration and rapping during the ignition transient besides rapid pressure rising. |
| Keywords: large aspect ratio solid rocket motor ignition transient integrated model |
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