N<sub>2</sub>O微推力器结构改进的仿真与试验分析

韩乐; 李茂; 方杰; 孙威; 蔡国飙

N₂O微推力器结构改进的仿真与试验分析

北京航空航天大学宇航学院,北京 100191

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出版历程
- 收稿日期: 2010-10-24
- 修回日期: 2010-12-13
- 刊出日期: 2011-09-28

Simulation and experimental analysis of structure improvement for nitrous oxide micro-thruster

School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 主要考虑影响比冲的温度因素,在原有N₂O微推力器结构上提出了改进方案,对改进前后N₂O微推力器推力室进行了三维流动传热耦合仿真,并采用改进后N₂O微推力器开展催化分解试验研究.对比分析后发现减少推力室向外的热量传递能维持较高的分解气体温度,从而利于提升N₂O微推力器比冲,并得到了影响微推力器比冲的结构参数,研究工作为N₂O微推力器的优化设计提供了有益参考.
- N₂O微推力器 /
- 结构设计 /
- 流场仿真 /
- 催化分解 /
- 比冲
Abstract: Many investigations were made on micro-thruster using nitrous oxide (N₂O).Based on the obtained results,the impact of the temperature on the specific impulse of the thruster was analyzed.An improved solution was presented to optimize the structure design of the former thruster.Both flow field simulation and experiment test of the improved device were carried out to compare with the result of the previous one,whereby the correlation between the structure and specific impulse was acquired.The results can provide some references for the research of the nitrous oxide micro-thruster.
- nitrous oxide micro-thruster /
- structure design /
- flow field simulation /
- catalytic decomposition /
- specific impulse

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参考文献(12)

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