电推进等离子体对航天器充放电效应的影响研究  

STUDY OF ELECTRIC PROPULSION PLUME INTERACTION ON SPACECRAFT SURFACE CHARGING

作　　者：冯娜[1] 李得天[1] 杨生胜[1] 陈益峰[1] 赵呈选[1] 汤道坦[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,兰州730000

出　　处：《真空与低温》2015年第5期297-302,共6页Vacuum and Cryogenics

摘　　要：电推进具有高比冲及低推进剂消耗等优点,被广泛用作地球同步轨道卫星南北位置保持和深空探测等任务的主推进系统。而电推进在轨工作产生的等离子体与地球同步轨道上的空间等离子体的特性截然不同,导致卫星的充放电过程更加复杂,影响卫星在轨安全运行。为此,电推进等离子体对航天器的影响是进行卫星电推进系统设计时需要关注的问题。主要讨论电推进羽流对航天器表面带电的影响,从理论研究、仿真模拟和地面试验三个方面对电推进系统对航天器表面充放电效应的研究进展进行了分析总结,最后对如何有效分析电推进等离子体羽流特性及其对航天器表面带电的影响的研究途径进行了展望。As an important form of advanced spacecraft propulsion technology,electric thruster is now widely developed and implemented to replace chemical system for modern spacecraft with high specific impulse.However,dense plume induced by electric propulsion thruster has high density and low energy which is quite different from space plasma on geosynchronous orbit.The difference between thruster and space plasma result in spacecraft surface charging becoming more complicated,which is research hotspots on abroad.In this paper,the effects of the electric propulsion plume on the spacecraft charging are discussed.The related numerical studies,in-flight test and software simulation are reviewed.Finally some suggestions are made for the research work in this field.

关 键 词：等离子体环境 电推进羽流 航天器表面带电 软件仿真 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]