Abstract: To meet the demands of aerospace missions for miniaturization, lightweight design, and high integration in electric propulsion systems, this paper proposes a novel integrated ignition/sustainment power supply solution for Hall electric propulsion systems. The design adopts aStwo-stage topological structure, integrating the functions of the traditional separate high-voltage ignition power supply and low-voltage constant-current sustainment power supply. The front stage employs aSforward isolated circuitSwith closed-loop control to achieve stable constant-current output. During the ignition phase, the rear stage utilizes aSBOOST converterSto provide a high voltage of approximatelyS300V. When output voltage drop is detected, the controller determines that ignition is successful, switches off the rear-stage boost circuit, and maintains stable constant-current output via the front stage. Experimental results demonstrate that the volume is reduced byS42%Scompared to traditional solutions, with weight decreased by 31% and efficiency improved toS90.8%. It outperforms conventional discrete power supplies in key metrics, offering an innovative solution for next-generation high-power-density electric propulsion systems.