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[1]王小永,张天平,江豪成,等.40 mN/3 000 s氙离子电推进系统工作性能在轨测试与分析[J].火箭推进,2015,41(01):76-81.
　WANG Xiao-yong,ZHANG Tian-ping,JIANG Hao-cheng,et al.In-orbit test and analysis of working performance for 40 mN/3 000 s xenon ion electric propulsion system[J].Journal of Rocket Propulsion,2015,41(01):76-81.
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40 mN/3 000 s氙离子电推进系统工作性能在轨测试与分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 41 期数: 2015年01期 页码: 76-81 栏目: 研究与设计 出版日期: 2015-04-30
Title:
In-orbit test and analysis of working performance for 40 mN/3 000 s xenon ion electric propulsion system
作者:
王小永; 张天平; 江豪成; 王少宁; 高 军
兰州空间技术物理研究所 真空技术与物理重点实验室 甘肃 兰州 730000
Author(s):
WANG Xiao-yong;  ZHANG Tian-ping;  JIANG Hao-cheng;  WANG Shao-ning;  GAO Jun
Key Laboratory of Vacuum Technology and Physics, Lanzhou Institute of Physics, CAST, Lanzhou 730000, China
关键词:
卫星; 氙离子电推进系统; 飞行试验; 工作性能; 在轨测试; 稳定性验证
Keywords:
satellite;  xenon ion electric propulsion system;  flight test;  operating performance;  in-orbit test;  stability demonstration
分类号:
V434-34
文献标志码:
A
摘要:
为获得电推进系统准确的工作性能，验证其在轨工作稳定性，国内首台空间用氙离子电推进系统于2012年11月～2014年2月在我国新技术试验卫星——实践九号A卫星上开展了首次在轨飞行试验。本文简要介绍了40 mN/3 000 s氙离子电推进系统的设计方案和主要性能指标，重点阐述了所开展的系统性能在轨测试内容、测试方法及获得的测试结果，并对测试结果进行了分析，最后给出了在轨测试结论。
Abstract:
To achieve accurate operating performance of electric propulsion system (EPS) and demonstrate its operating stability in orbit, flight tests of Chinese first xenon ion EPS used in space were carried out for the first time at the SJ-9A satellite from November 2012 to February 2014. The design scheme and primary performance index of the 40 mN/3000 s xenon ion EPS are introduced briefly in this paper. The in-orbit performance test contents, methods and results of the system are described emphatically. The achieved test results are analyzed. The conclusions of in-orbit test are brought out.

参考文献/References:

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备注/Memo

收稿日期：2014-10-29；修回日期：2014-12-09 作者简介：王小永（1968—），男，高级工程师，硕导，研究领域为空间电推进技术与产品设计

更新日期/Last Update: 1900-01-01