Recent advancements in science and technology have enabled even microsatellites to perform various high-level tasks. As the range of missions that satellites undertake expands, even microsatellites now require thrust systems for orbit adjustment and collision avoidance. In such satellite applications, sizes and weights of all electrical components and propulsion systems are restricted, emphasizing the importance of miniaturization and weight reduction. Research is ongoing in various methods to address these needs. To solve these challenges, this study proposed a design model for miniaturizing and lightening both Anode Power Module (APM) and gas supply system. The APM utilizing an LLC resonant converter achieved an efficiency of up to 86%. An evaluation of flow control characteristics of the proposed gas supply device showed that the flow control error was less than 2.3%, indicating effective results. A thermal mass flow sensor was developed to measure the flow of gas. Temperature characteristics derived from experiments were analyzed to assess their applicability to electric thruster systems for satellites.