真空热试验中离子推进器点火对真空系统的影响与对策  

Influence of Ion-Thruster Igniting on Pressure in Thermal Vacuum Test and Possible Solutions

作　　者：李培印[1] 柳晓宁[1] 刘春[1] 杜春林[1] 

机构地区：[1]北京卫星环境工程研究所,北京100094

出　　处：《真空科学与技术学报》2014年第8期836-841,共6页Chinese Journal of Vacuum Science and Technology

摘　　要：离子推进器(也称离子发动机、离子推力器)在航天领域有着广泛的应用,本文简要介绍了其工作原理。在真空热试验中,离子推进器点火,会向真空室内喷射出高能粒子,严重影响容器真空度。本文依据真空系统抽气方程,绘制出了推进器点火过程中的理论抽气曲线。试验结果显示,对氩气的实际抽气曲线与理论计算结果吻合很好,而对氙气则不太理想。本文对此展开分析,同时提出了采用氙气泵来有效抽除氙气的方法。We addressed the impact ofigniting of ion-thrusteron the vacuum system, including but not limited to the emission of high energy particles, ion sputtering, gas desorption and film deposition, on the vacuum system in thermal vac- uum test of spacecraft. The igniting of ion-thruster in vacuum chamber was physically modeled, analytically calculated based on the extraction equation of the vacuum system, and experimentally evaluated. The time evolution of the pressure during igniting of ion thruster, or noble gas extraction curve, was calculated and plotted. The experimental results show that the calculated extraction curve for argon agrees well with the measured one,but does a poor job for xenon because the pumping speed of conventional cryogenic pump for xenon is too low. We suggest that a dedicated xenon cryogenic pump may be a good solution.

关 键 词：真空热试验 离子推力器 点火 氙气泵 

分 类 号：V1[航空宇航科学与技术—人机与环境工程]