Abstract: The interaction of spacecraft with space plasma, high-energy particles, and geomagnetic field can cause charge-discharge effect, which will seriously affect the space missions. Emitting artificial plasma through plasma source can effectively control the potential to ensure the safety of spacecraft operation, which is more flexible and efficient than other potential control methods; however, the research literature from domestic researchers is rarely available. Therefore, a theoretical analysis of spacecraft charging based on the spacecraft current balance equation and a spherically symmetric model of the plasma source potential control theory are presented.Furthermore, the effects of space plasma and human-artistic plasma on spacecraft potential were simulated and analyzed by the SPIS (spacecraft plasma interaction system) simulation platform. It is shown that, under the action of space plasma in GEO orbit, unequal charges exist on different material surfaces of spacecraft, and the potential can reach −14 000 V. The plasma source work can efficiently control the spacecraft within −10 V. Based on the above study, ground simulation experiments were carried out. The results show that the −6000 ~ −5000 V surface voltage of the spacecraft simulator can be controlled to 0 V within seconds by using the plasma source controller, the controller is suitable for installation on the east side of the satellite, and its net emission current directly affects the control effect. The technology has good control effect on both high potential and unequal charge on spacecraft surface within seconds, and the above research results will provide support for the space engineering application.