Development of a 300-W class Hall-effect thruster for small satellites
- Paper number
IAC-09.C4.P.16
- Author
Prof. Jongho Seon, Satrec Initiative, Korea, Republic of
- Coauthor
Mr. Seongmin Kang, Satrec Initiative, Korea, Republic of
- Coauthor
Mr. Jongsub Lee, Korea Advanced Institute of Science and Technology (KAIST), Korea, Republic of
- Coauthor
Prof. Wonho Choe, Korea Advanced Institute of Science and Technology (KAIST), Korea, Republic of
- Coauthor
Dr. Hitoshi Kuninaka, Japan Aerospace Exploration Agency (JAXA), Japan
- Year
2009
- Abstract
A small hall thruster with a thrust of about 7-9 mN and a specific impulse of about 1500 s is being developed with an intent to control or maintain the orbits of small satellites. The development is a continued effort between Satrec Initiative of Korea and Emirate Institute for Advanced Science and Technology of Dubai from its precedent mission for enhanced Earth imaging and technology development. The total mass, consumed electric power and efficiency of the thruster are approximately 15 kg, 300W and 30\%, respectively. The thruster system consists of a hall thruster with a cylindrical or semi-annular cross section, a power processing unit and a Xenon (Xe) gas feed system. A $\mu$μ-wave cathode that is modified from those flown on Hayabusa mission has been adapted for ground demonstration of the thruster operation. To investigate the thrust performance, a pendulum type thrust stand is used, which utilizes two independent thrust measurement techniques using a gap sensor and the newly-developed mirror-PSD position measurement method. The plasma plume angle is measured by a Faraday probe mounted on a rotational motion stand inside the vacuum chamber. Results of the thruster operation in the laboratory and the design of qualification model of the thruster subsystem will be discussed along with a brief introduction to this international collaboration.
- Abstract document
- Manuscript document
IAC-09.C4.P.16.pdf (🔒 authorized access only).
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