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[1]孙成,方杰,郑力铭,等.N20微推力器性能及喷管热结构分析[J].火箭推进,2008,34(05):5-9.
　Sun Wei,Fang Jie,Zheng Liming,et al.N20 micro-thruster performance and the nozzle thermo-structure analysis[J].Journal of Rocket Propulsion,2008,34(05):5-9.
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N20微推力器性能及喷管热结构分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 34 期数: 2008年05期 页码: 5-9 栏目: 研究与设计 出版日期: 2008-10-30
Title:
N20 micro-thruster performance and the nozzle thermo-structure analysis
作者:
孙成; 方杰; 郑力铭; 蔡国飙
北京航空航天大学宇航学院，北京100083
Author(s):
Sun Wei; Fang Jie; Zheng Liming; Cai Guobiao
School of Astronautics，Beijing Univ．of Aeronautics and Astronautics，Beijing 100083，China
关键词:
氧化亚氮; 微推力器; 喷管; 有限元分析
Keywords:
nitrous oxide; micro-thruster; nozzle; finite element analysis
分类号:
V439.7
文献标志码:
A
摘要:
针对采用氧化亚氮推进剂的单组元微推力器开展了比冲性能影响因素的分析． 分析结果显示微推力器比冲与氧化亚氮分解效率及喷管扩张比有着密切关系。利用有限元分 析法对高空及地面试验两种工况下氧化亚氮单组元微推力器喷管的结构温度场开展了数值仿 真计算，并在结构温度场仿真计算的基础上进一步对地面试验用喷管的结构应力场进行了分 析。初步试验表明，所设计的微喷管在地面工况下工作良好。
Abstract:
Performance analysis for monopropellant micro-thruster using nitrous oxide(N20) propellant was conducted based on the thermodynamic computation．Preliminary results show that decomposition rate of nitrous oxide and the expansion ratio of nozzle both effected the specific impulse of the thruster．Finite element analyses on temperature field of micro-nozzle were conducted respectively under vacuum and ground conditions．Subsequently，analysis on stress field of nozzle for ground test Was conducted．Results of simulation show that peak value of temperature and stress both appear at the throat section of the nozzle．Preliminary experiments under ground condition have testiffed the reliability of the micro-nozzle．

参考文献/References:

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[7]Guobiao Cai，Wei Sun。Jie Fang，et a1．Initial Results of BUAA Nitrous Oxide Micro-thruster Research[C]．58th International Astronautical Congress，Hyderabad，India, 2007．

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备注/Memo

收稿日期：2008-08—13；修回El期：2008-09—10。 作者简介：孙威(198l一)，男，博士，研究领域为N20单组元微推进系统。

更新日期/Last Update: 1900-01-01