| 引用本文: | 宋志兵,王振国,张炜,等.H2O2/HTPB固液混合发动机点火试验研究.[J].国防科技大学学报,2008,30(1):28-31.[点击复制] |
| SONG Zhibing,WANG Zhenguo,ZHANG Wei,et al.Experimental Investigation on Ignition of H2O2/HTPB Hybrid Rocket Engine[J].Journal of National University of Defense Technology,2008,30(1):28-31[点击复制] |
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| H2O2/HTPB固液混合发动机点火试验研究 |
| 宋志兵, 王振国, 张炜, 夏智勋, 胡建新 |
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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: |
| 利用H2O2催化分解原理，设计了烃类燃料在催化分解的90% H2O2中能燃烧的点火器，然后采用该点火器进行H2O2/HTPB固液混合发动机点火试验研究。试验结果表明，该点火器能够成功启动H2O2/HTPB固液混合发动机，且当混合比偏离最佳混合比后，发动机的燃烧效率降低。 |
| 关键词: 固液混合发动机 燃烧过程 点火试验 固液混合推进剂 |
| DOI： |
| 投稿日期：2007-09-14 |
| 基金项目:国家863基金资助项目(2007AA702312) |
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| Experimental Investigation on Ignition of H2O2/HTPB Hybrid Rocket Engine |
| SONG Zhibing, WANG Zhenguo, ZHANG Wei, XIA Zhixun, HU Jianxin |
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(College of Aerospace and Materials Engineering, National Univ. of Defense Technology, Changsha 410073, China)
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| Abstract: |
| An innovative igniter based on catalytic decomposition of H2O2 was designed and manufcatured. With this igniter, an H2O2/HTPB hybrid rocket engine was tested. The experiment results demonstrate that this new igniter can successfully start the H2O2/HTPB hybrid rocket engine with combustion stability and good performance. The experiment results also show that the combustion efficiency will achieve the highest level when the hybrid ratio deviates from the best ratio of oxidizer. |
| Keywords: hybrid rocket engine combustion process ignition experiment hybrid propellant |
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