Year: 2025
Type: article
Abstract: With the increasing demand for microsatellites, research on low-power electric thrusters suitable for satellites has been actively conducted.In this study, a conceptual design of an RF ion thruster for microsatellites was performed.The mission orbit for a 6U CubeSat was defined, and the propulsion system requirements were analyzed to utilize argon as the propellant and to operate with 20 W of RF power, ensuring a thrust of approximately 0.3 mN and a specific impulse of 1500 s.A detailed conceptual design of the RF ion thruster, including the grid system and plasma generation chamber, was conducted under the given constraints.Consequently, the thruster was designed to generate a thrust of 0.3 mN and a specific impulse of 1530 s at an argon flow rate of 0.35 sccm.
Source: Journal of Propulsion and Energy
Authors: Jeongho Kim, Jiwoong Jung, Junwoo Jung, Kyungmi Park, Woojin Joung, Sanghoo Park, Dong-Hyun Cho, Holak Kim
Language: English
Subfield: Electrical and Electronic Engineering
Field: Engineering
Domain: Physical Sciences
Open Access status: hybrid
OpenAlex ID: W4411331848