等离子体源型电位主动控制器特性分析

Characteristics Analysis of Plasma Source Potential Active Controller

研究了基于等离子体发射装置的航天器电位主动控制技术,对航天器在轨运行时表面充电和电位主动控制过程进行了分析与计算,并通过建立等离子体源型电位主动控制器在工作过程中净发射电流与悬浮电位之间的关系对其性能进行描述,在此基础上,讨论了等离子体温度、离子电流及阳极电压等因素对控制器控制效果的影响。分析结果表明:利用等离子体源型电位主动控制器发射低温等离子体束流对航天器电位进行主动控制,可在保持较大净发射电流的同时,将航天器悬浮电位控制在较小的水平;相同净发射电流条件下,较高的等离子体温度、较大的离子电流及较小的阳极电压有助于将航天器悬浮电位控制在更小的水平,实现更好的控制效果。

In this paper,the active control technology of spacecraft potential based on plasma emitter is studied.The surface charging and active control of potential of spacecraft in orbit are analyzed and calculated,and the relationship between net emission current and floating potential of plasma source potential active controller is established to describe its performance.On this basis,the effects of different artificial plasma temperature,ion current,and anode voltage on the control effect of the controller are discussed.The results show that the spacecraft floating potential can be controlled at a small level while maintaining a large net emission current by using the plasma source potential active controller to launch a low temperature plasma beam to actively control spacecraft potential.Under the same net emission current,higher plasma temperature,higher ion current and lower anode voltage can help to control the spacecraft floating potential at a smaller level and achieve better control effect.