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자료유형
학술저널
저자정보
(Pusan National University) (Pusan National University) (Pusan National University) (Pusan National University) (Korea Advanced Institute of Science and Technology) (Korea Advanced Institute of Science and Technology) (Pusan National University) (Pusan National University)
저널정보
한국추진공학회 Journal of Propulsion and Energy Journal of Propulsion and Energy Vol.5 No.1
발행연도
수록면
75 - 88 (14page)

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초록· 키워드

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.
#RF ion thruster #Low-power electric propulsion #Microsatellite
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목차

  1. ABSTRACT
  2. 1. Introduction
  3. 2. Requirements for the Propulsion System
  4. 3. Design of the Ion thruster
  5. 4. Conclusion & Future Work
  6. References

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