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도근태(Guentae Doh),김영호(Youngho Kim),이동호(Dongho Lee),박재홍(Jaehong Park),최원호(Wonho Choe) 한국추진공학회 2021 한국추진공학회 학술대회논문집 Vol.2021 No.5
홀추력기는 전기추력기의 일종으로 소모전력 대비 추력이 높고 비추력 또한 큰 편으로 저궤도 위성과 정지궤도 위성의 추진 장치로서 널리 사용되고 있다. 특히, 최근에는 민간기업들이 소형위성의 저궤도 군집비행 사업에 진출하고 위성 군집비행의 활용도가 갈수록 높아짐에 따라 위성용 전기추력기의 수요가 크게 증가하고 있다. 본 연구에서는, 소형위성에 활용될 수 있는 700 W급 홀추력기 랩모델 설계 및 제작, 성능측정 결과를 소개한다. 그 결과, 양극전력 620 W에서 추력 38 mN, 통합비추력 1540s, 양극효율 50%의 성능이 확인되었다. A Hall thruster is a type of electric propulsion that has been widely employed as a space propulsion device for LEO and GEO satellites, which has advantages on the high thrust to power and moderate specific impulse. The demand for electric propulsion for satellites is rapidly growing as the high utilization of satellite constellation has emerged. In this paper, we report the development and performance measurement of a 700 W class laboratory model Hall thruster. The measured performance parameters were 38.5 mN thrust, 1540 s total specific impulse, and 50% anode efficiency at 620 W anode power.
도근태(Guentae Doh),김영호(Youngho Kim),이동호(Dongho Lee),박재홍(Jaehong Park),최원호(Wonho Choe) 한국추진공학회 2021 한국추진공학회지 Vol.25 No.5
700 W class laboratory model Hall thruster, which can be used for the orbit control or station keeping of small satellites, was developed. The size of the discharge channel was determined using a scaling law, and the magnetic field was designed to be symmetric with respect to the midline of the discharge channel and to be maximized outside the discharge channel. Base pressure of a vacuum chamber was maintained below 2.0×10<SUP>-5</SUP> Torr during experiments, and the thrust was measured by a thrust stand. The anode flow rate and coil current were varied with the fixed anode voltage at 300 V. Under the operation condition at 2.36 ㎎/s anode flow rate and 2.4 A coil current, performance was optimized as 38 mN thrust, 1,540 s total specific impulse, and 50 % anode efficiency at 620 W anode power.