Abstract: This paper analyzes and optimizes the method of equipotential control on the surface of the multilayer heat insulation of an electromagnetic monitoring satellite in the space plasma charging environment of the satellite and with consideration of its surface equipotential requirements. The desirable working processes for the multilayer components are proposed, including the fabrication, the installation, the grounding, the detection, and the protection, to meet the requirement of controlling the surface potential difference of the whole satellite within ±2V.