DEVELOPMENT AND EXPERIMENTAL VALIDATION OF A FULLY-ELECTRODELESS ELECTRIC PROPULSION SYSTEM FOR SATELLITE OPERATIONS IN LOW EARTH ORBIT

This paper presents the design, fabrication, and experimental validation of disruptive Electric Propulsion (EP) system. The system features a compact helicon reactor integrated with a multi-dipole cusp magnetic confinement system, aligning with the emerging trends in the Low Earth Orbit (LEO) propulsion sector. This approach aims to meet the increasing demands for efficient, compact, and sustainable propulsion solutions suitable for modern satellite missions. This research aims to enhance the throttleability of a compact Helicon Plasma Thruster (HPT) by managing ion energies via transitions from Capacitive Coupled Plasma (CCP) modes to Inductive Coupled Plasma (ICP) modes. This was achieved by adjusting the RF input power while maintaining a constant magnetic field. Through the experimental testing campaign, it has been proved the jump power threshold of the CCP-ICP at 200 W for an argon flow rate of 8 standard cubic centimeter per minute (sccm) by means of Optical Emission Spectroscopy. The findings provide guidelines for further optimization of the HPT, aiming to achieve a comprehensive understanding of the argon plasma structure inside a compact magnetically enhanced inductively reactor. © 2024, Politechnica University of Bucharest. All rights reserved.