Electrical Power and Propulsion System Architecture for a 75 Kg Microsatellite Hall-effect Thruster

This paper presents a comprehensive system-level design for the electrical power and electric propulsion subsystems in microsatellites. The study begins with an overview of the subsystems typically integrated into microsatellite platforms, before focusing in greater detail on electrical power distribution and electric propulsion. Particular attention is given to the Hall Effect Thruster (HET), including its operating principle, advantages, and inherent limitations. A three-year mission scenario is considered to estimate annual velocity changes and corresponding power requirements, providing a realistic operational framework. The analysis incorporates orbital mechanics by examining the relationship between the Sun and satellite in terms of Earth’s radius, gravitational constant, mass, and eclipse duration. Satellite velocity is calculated across different orbital geometries, with additional consideration of drag forces that may arise in low Earth orbit. Building on this foundation, the paper concentrates on the design of a miniaturized HET tailored for a 75 kg satellite operating in a 1000 km circular orbit. Key design parameters such as thrust requirements, power demands, propellant selection, and component sizing are systematically evaluated. The proposed system enables small-scale orbital maneuvers through continuous monitoring of orbital velocity and feedback-based corrections. Furthermore, the paper details strategies for power distribution among subsystems and identifies the fundamental components required for implementation. By integrating propulsion and power considerations at the system level, the study demonstrates a viable pathway for enhancing the autonomy and maneuverability of microsatellites in extended missions.