Theory study of ion thruster plume to spacecraft surface charging

被引：0
|
作者：
Feng N. [1 ]
Li D. [1 ]
Yang S. [1 ]
Chen Y. [1 ]
Zhao C. [1 ]
Tang D. [1 ]
机构：
[1] Lanzhou Space Technology Physics Institute, Lanzhou
来源：
Li, Detian | 1600年 / Science Press卷 / 42期
关键词：
Charge and discharge balance equation; Charge-exchange ion; Electric thruster; Geosynchronous orbit; Space plasmas; Surface charging;
D O I：
10.13336/j.1003-6520.hve.20160412008
中图分类号：
学科分类号：
摘要：
Microthermal dense plasma is induced when electric propulsion thruster is working on the orbit, which is quite different from space plasma on geosynchronous orbit. The difference between thruster and space plasma may ensure spacecraft surface charging to become more complicated. Moreover, the charge-exchange (CEX) ion which exists in ion plasma is influenced by spacecraft surface potential, and it may form backflow and induce surface charge and discharge. Therefore, focusing on material secondary electron and backscattered electron emission current, we analyzed physic characteristics of the thruster plasma, and put forward a computation method of the surface charge potential by using charge and discharge balance equation. The research results reveal that the spacecraft surface is influenced by plasma on geosynchronous orbit, and the potential reaches -104 V during periods of geomagnetic activity. And the thruster plasma current is 10-3 A/m2 (which is much higher than space plasma changing current) when the thruster plasma is working. It is the main reason why the spacecraft surface get charged. Moreover, the thruster plasma can neutralize the spacecraft surface potential to -10 V, which means the backflow and neutralization electron current can release damage effect caused by spacecraft charging. © 2016, High Voltage Engineering Editorial Department of CEPRI. All right reserved.
引用
收藏
页码：1449 / 1454
页数：5
相关论文
共 20 条
  • [1] Zhang T., Recent international progress in ion and hall electric propulsions, Vacuum & Cryogenics, 12, 4, pp. 187-193, (2006)
  • [2] Dudzinski L.A., Pencil E.J., Electric propulsion requirements and mission analysis under NASA's in-space propulsion technology project, 30th International Electric Propulsion Conference, pp. 25-32, (2007)
  • [3] Pencil E.J., Recent electric propulsion development activities for NASA science mission, IEEE Aerospace Conference, pp. 1-9, (2009)
  • [4] Wang S., Yi Z., Tang X., Et al., Analysis of exposed dielectric bulk charging in geosynchronous orbit environment via computer simulation, High Voltage Engineering, 41, 2, pp. 687-692, (2015)
  • [5] Mizera P.F., Leung M.S., A review of SCATHA (spacecraft charging at high altitudes) satellite results: charging and discharging, pp. 82-129, (1985)
  • [6] Olsen R.C., Record charging events from applied technology satellite 6, Journal of Spacecraft, 24, 4, pp. 362-366, (2012)
  • [7] Bogorad A., Bowman C., Herschitz R., Et al., Differential charging control on solar array for geosynchronous spacecraft, IEEE Transactions on Nuclear Science, 40, 6, pp. 1542-1546, (1993)
  • [8] Tajmar M., Sedmik R., Scharlemann C., Numerical simulation of Smart-1 hall-thruster plasma interactions, Journal of Propulsion and Power, 25, 6, pp. 1178-1188, (2009)
  • [9] Likar J.J., Interaction of charged spacecraft with electric propulsion plume: on orbit date and ground test result, IEEE Transactions on Nuclear Science, 53, 6, pp. 345-356, (2006)
  • [10] Katz I., Mandell M., Jongeward G., Et al., The importance of accurate secondary electron yields in modeling spacecraft charging, Journal of Geophysical Research, 91, 1, (1986)
12