40mN/3000s氙离子电推进系统工作性能在轨测试与分析  

In-orbit test and analysis of working performance for 40mN/3000s xenon ion electric propulsion system

作　　者：王小永[1] 张天平[1] 江豪成[1] 王少宁[1] 高军[1] 

机构地区：[1]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

出　　处：《火箭推进》2015年第1期76-81,共6页Journal of Rocket Propulsion

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40mN/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。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.

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 

分 类 号：V434-34[航空宇航科学与技术—航空宇航推进理论与工程]