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Development of a 700 W Class Laboratory Model Hall Thruster

700 W급 홀 전기추력기 랩모델 연구개발

  • Doh, Guentae (Department of Physics, Korea Advanced Institute of Science and Technology, KAIST) ;
  • Kim, Youngho (Department of Nuclear and Quantum Engineering, KAIST) ;
  • Lee, Dongho (Department of Physics, Korea Advanced Institute of Science and Technology, KAIST) ;
  • Park, Jaehong (Space Exploration Engineering Program, Department of Aerospace Engineering, KAIST) ;
  • Choe, Wonho (Department of Nuclear and Quantum Engineering, KAIST)
  • Received : 2021.06.04
  • Accepted : 2021.09.05
  • Published : 2021.10.31

Abstract

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 2.0×10-5 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 mg/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.

소형위성의 궤도조정 및 궤도유지에 활용될 수 있는 700 W급 홀추력기 랩모델을 개발하였다. 스케일링 방정식을 사용하여 방전채널의 크기를 선정하였으며, 자기장이 방전채널 중심선을 기준으로 대칭성을 가지면서 방전채널 바깥에서 최대가 되도록 설계하였다. 개발된 홀추력기의 방전시험은 2.0×10-5 Torr 이하의 배경압력을 갖는 진공 환경에서 수행되었으며 추력 스탠드를 이용하여 추력을 측정하였다. 양극전압을 300 V로 고정하고 양극유량과 코일전류를 변수로 하여 추력을 측정하였으며, 양극유량 2.36 mg/s, 코일전류 2.4 A 조건에서 양극전력 620 W에서 추력 38 mN, 통합비추력 1,540 s, 양극효율 50 %로 가장 높은 성능을 보였다.

Keywords

Acknowledgement

본 연구는 방산기술지원센터 주관의 국방무기 체계 핵심기술과제(응용연구)인 '고효율 소형 추력기 설계기술' 과제의 일환으로 수행되었습니다. 또한 KAIST에 ANSYS 라이센스를 제공해준 ANSYS Korea에 감사를 표합니다.

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