| 200N LOX/MMH推力系统方案论证 |
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| 引用本文： | 张忠利.200N LOX/MMH推力系统方案论证[J].火箭推进,2009,35(3):15-20. |
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| 作者姓名： | 张忠利 |
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| 作者单位： | 西安航天动力研究所,陕西,西安,710100 |
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| 摘 要： | 论证了200N LOX/MMH动力系统的方案,提出了该系统方案的结构设计参数,并对该结构进行了传热及流场分析。通过传热及流场分析得到：200N LOX/MMH推力系统在方案上是可行的,在满足可靠冷却的前提下比冲达到3170m/s,比目前应用的小姿控动力系统高。
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| 关 键 词： | LOX/MMH 推力系统 |
Investigation on the scheme of 200N LOX/MMH thrust system |
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| Zhang Zhongli.Investigation on the scheme of 200N LOX/MMH thrust system[J].Journal of Rocket Propulsion,2009,35(3):15-20. |
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| Authors: | Zhang Zhongli |
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| Institution: | Xi'an Aerospace Propulsion Institute;Xi'an 710100;China |
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| Abstract: | The scheme of 200N LOX/MMH thrust system was investigated,and configuration parameters were gained.The heat transfer and the flow-field were analyzed.The analysis results showed that the scheme of 200N LOX/MMH thrust system was feasible,the specific impulse can reach 3170m/s,which is higher than that of present used system. |
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| Keywords: | LOX/MMH |
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