真空弧推力器技术研究  

STUDY ON VACUUM ARC THRUSTER TECHNOLOGY

作　　者：吴先明[1] 张天平[1] 任亮[1] 陈新伟 WU Xian-ming;ZHANG Tian-ping;REN Liang;CHEN Xin-wei(Science and Technology on Vacuum Technology and Physics Laboratory,Lanzhou Institute 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》2017年第6期331-335,共5页Vacuum and Cryogenics

基　　金：国防基础科研项目(JCKY2016203C043);装备预研重点实验室基金(61422070306)

摘　　要：微纳卫星因其简单、经济、可靠越来越广泛应用于空间任务,传统的推进系统通常不能应用于微纳卫星平台。真空弧推力器(VAT)是一种利用真空中正负极之间放电产生等离子体射流的电推进装置,适用于微纳卫星的理想电推进类型,具有比冲高、效率高、质量小和使用固态推进剂等优点。介绍了同轴型和环型真空弧推力器系统方案及实验测试结果,针对环型真空弧推力器开展了数值计算研究,利用PIC方法重点考察了磁场对推力器性能的影响,主要包括磁场对等离子体密度分布和离子速度分布的影响;实验测试包括电参数测试、离子速度测量和微小推力器测量等,结果表明真空弧推力器具有良好的性能。Micro-nano satellite is more and more widely used in space missions for its simplicity,cost-effective and reliability.Traditional propulsion system is not suitable for such satellite platform.Vacuum Arc Thruster(VAT)is one kind of electric propulsion device which generates plasma jet utilizing the discharge between cathode and anode in vacuum,it is the ideal kind of electric propulsion suitable for micro-nano satellite.This kind of propulsion has the advantages of high specific impulse,high efficiency,low mass and using solid propellant.In this paper,system schemes and experimental results for coaxial and ring vacuum arc thruster are presented.Numerical simulations are carried out for ring electrode vacuum arc thruster.The affects of the magnetic field on the thruster's performance are studied using PIC method,including the influence of the magnetic field on the plasma density distribution and ion velocity.Experimental tests include electric parameter measurement,ion velocity measurement and tiny thrust measurement,the testing results indicate that the vacuum arc thruster has good performance.

关 键 词：微纳卫星 真空弧推力器 等离子体 粒子密度分布 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]