同轴型真空电弧推力器理论设计研究  

THE THEORETICAL DESIGN OF CO-AXIAL VACUUM ARC THRUSTER

作　　者：任亮[1] 张天平[1] 吴先明[1] REN Liang;ZHANG Tian-ping;WU Xian-ming(Science and Technology on Vacuum Technology and Physics Laboratory,Lanzhou Insitute of Physics,Lanzhou 730000,China)

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,兰州730000

出　　处：《真空与低温》2016年第6期354-358,共5页Vacuum and Cryogenics

基　　金：中国空间技术研究院CAST基金项目(YJJ0701);兰州空间技术物理研究所自主研发项目(YSC0716)

摘　　要：随着包括立方体卫星在内的微纳卫星平台技术的迅猛发展,应用真空电弧推力器作为其姿态控制和轨道转移的微推进系统得到了研究人员的重视,对真空电弧推力器的理论设计研究也开展了大量的工作。针对同轴型真空电弧推力器的理论设计,在深入调研国外相关设计理论和计算方法的基础上,介绍了基于经验的性能预测模型,对推力器设计参数和工作性能指标之间的关系进行了分析,可以为同轴型真空电弧推力器在初步方案设计时的初始参数选取和工作性能计算提供参考和依据。With the development of micro/nano-satellite platform including Cubesat platform,the application of Vacuum Arc Thruster(VAT)as the micro-propulsion system of attitude control and orbital maneuver gains attention of researchers,and a lot of study on theoretical design of VAT were carried out. This paper aimed at Co-axial VAT and reviewed on the design theory and calculation method abroad around co-axial VAT design. A semi-empirical performance model was introduced and the relationship between design parameters and working performance was also analyzed,which would serve the initial parameters selection and working performance calculation of co-axial VAT in first step design.

关 键 词：真空电弧 微推力器 同轴型 设计参数 预测模型 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]