Abstract: Hall thrusters offer numerous advantages for spacecraft propulsion, including high efficiency, high specific impulse, long service life, and high reliability. These characteristics make them particularly suitable for long-duration missions requiring precise and sustained thrust. In recent years, Hall thrusters have been widely adopted for various spacecraft operations, such as attitude control, orbital position maintenance, and orbit transfer maneuvers. Their increasing application underscores their importance in both commercial and scientific space missions. However, a significant challenge associated with Hall thrusters arises from their underlying working principle. During operation, they generate discharge disturbances with frequency components spanning from tens of kilohertz up to several gigahertz. These disturbances, if not properly managed, can lead to various operational anomalies. In mild cases, they may cause unstable thrust output, affecting mission accuracy. In more severe scenarios, such perturbations can cause thruster shutdown or the generation of instantaneous high-current pulses. These high-current transients can propagate through electrical cables to the satellite’s primary power bus, potentially causing voltage spikes, electromagnetic interference, or even damage to sensitive electronic components. Such events pose a serious risk to the overall stability and reliability of the spacecraft's power supply system. Given these potential impacts, it is essential to implement appropriate mitigation strategies to address discharge disturbances in Hall thrusters. This paper begins by examining the fundamental mechanisms behind discharge disturbances in Hall thrusters. It then presents a detailed analysis of the characteristics of high-current pulse discharges generated during operation. Based on this analysis, protective measures are proposed from both software and hardware perspectives within the power processing unit. The effectiveness of these protective measures is verified through a combination of simulation studies and experimental tests. The results provide an engineering reference for ensuring the safe and reliable integration of Hall thrusters into spacecraft systems.