摘要
推进器喷射过程中在尾部形成羽流区,羽流区域发生电荷交换碰撞,产生的电荷交换(charge exchange,CEX)离子与航天器表面相互作用,对在轨运行的航天器产生羽流污染效应.基于SPT100霍尔推进器建立了完整的航天器三维仿真模型,在满足准中性假设的条件下,采用PIC-MCC方法,通过模拟和计算航天器表面电势分布、电荷交换碰撞后的CEX离子电荷密度分布以及束流离子电荷密度分布规律,分析了CEX离子对航天器表面充放电的影响以及造成的羽流污染影响区域范围,为霍尔推进器系统的进一步优化设计提供理论参考.
In the plume area formed in the tail during the ejection of the thruster,the charge exchange(CEX)ions generated after the charge exchange collision interact with the surface of the spacecraft.During this process,it can easily lead to plume pollution effects on the spacecraft in orbit.For the Hall thruster,a complete three-dimensional model of the spacecraft is established based on the SPT100 thruster.Based on the quasi-neutral assumption,the PIC-MCC method is used for the simulation.The calculation results give the surface potential distribution of the spacecraft and the charge exchange collision including CEX ion distribution and beam ion distribution.The result shows the impact of CEX ions on spacecraft surface charging and discharging as well as the range of the plume pollution influence area.It is useful for the further optimization of the Hall thruster system.
作者
贾帅
赵强
郝建红
范杰清
张芳
董志伟
JIA Shuai;ZHAO Qiang;HAO Jianhong;FAN Jieqing;ZHANG Fang;DONG Zhiwei(School of Electrical and Electronic Engineering,North China Electric Power University,Beijing 102206,China;Beijing Institute of Applied Physics and Computational Mathematics,Beijing 100094,China)
出处
《河北师范大学学报（自然科学版）》
CAS
2021年第5期460-468,共9页
Journal of Hebei Normal University：Natural Science
基金
国家自然科学基金(U1730247)。
