离子发动机真空热试验技术  

Ion-thruster technology in thermal vacuum test

作　　者：李培印[1] 冯尧[1] 李天水[1] LI Pei-yin FENG Yao LI Tian-shui(Beijing Institute of Spacecraft Environment Engineering, Beijing 100094, China)

机构地区：[1]北京卫星环境工程研究所,北京100094

出　　处：《真空》2017年第4期42-47,共6页Vacuum

摘　　要：离子发动机(又名离子推进器、推力器)在航天领域有着广泛的应用,本文简要介绍了其工作原理与结构。在真空热试验中,离子发动机点火,会向真空室内喷射出高能Xe粒子,对卫星、热沉、容器压力等均会产生不良影响。本文结合具体的离子发动机真空热试验结果,对发动机点火的影响进行了分析,并提出了针对性的解决方案。我们使用氙泵来提升系统抽气能力,安装防溅射靶吸收并抑制高能粒子。Ion-thruster has been widely employed in the aerospace applications. In this paper, the structure and working principle of the ion-thruster were introduced. In the satellite thermal vacuum test, high energy Xe particles emitted by ion-thruster ignition were observed. The ignition effects on the satellite, heat sink, pressure of chamber were analyzed based on the thermal vacuum test results. To solve this problem, Xe pump was used to improve the pumping speed, and anti-sputtering targets were installed to absorb the high energy particles.

关 键 词：电推进 氙气 氙泵 防溅射靶 

分 类 号：TH122[机械工程—机械设计及理论] TH132.4