초소형위성용 전계방출 전기추력기의 바늘형 방사기 설계를 위한 이론모델 개선 연구

Recently, with the increasing demand for CubeSat worldwide, various propulsion systems for CubeSat are being developed. Among them, Field Emission Electric Propulsion (FEEP) thruster is preferred as a propulsion system for CubeSat due to simplicity, miniaturization, and high efficiency. From previous studies, it is found that a theoretical model for the current-voltage characteristics of FEEP thrusters has conventionally been used to predict their performance. Therefore, in this study, we derived a theoretical model for the needle emitter to verify errors in the existing theoretical model and validate its reliability. Furthermore, through comparison with experimental measurements, we discovered inaccuracy and limitations in the existing theoretical model, and based on this analysis, we established and proposed an improved theoretical model to enhance accuracy. The use of the improved theoretical model is expected to enhance the prediction of performance and reliability in the design of FEEP thrusters.