Performance characteristics of very low power cylindrical Hall thrusters for the nano-satellite “PROITERES-3” |
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| Affiliation: | 1. Osaka Institute of Technology, 5-16-1 Omiya, Asahi-Ku, Osaka 535-8585, Japan;2. Osaka University, Toyonaka, Osaka 560-8531, Japan;1. School of Instrumentation and Optoelectronic Engineering, Beihang University, Beijing 100191, China;2. School of Space and Environment, Beihang University, Beijing 100191, China;3. School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China;4. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;5. School of Astronautics, Beihang University, Beijing 100191, China;1. The University of Tokyo, Bunkyo-ku, Tokyo, 113-8656, Japan;2. Japan Aerospace Exploration Agency / Institute of Space and Astronautical Science (JAXA/ISAS), Chuo-ku 3-1-1, Sagamihara-City, Kanagawa, 252-5210, Japan;3. Kyushu University, 6-1 Kasuga-kouen, Kasuga, Fukuoka, 816-8580, Japan |
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| Abstract: | Development of Hall thrusters for nano, small and low power satellites below 100 W is expected. In lowering Hall thruster power, the cylindrical type Hall thruster is more advantage than conventional coaxial-type Hall thrusters. In this study, a very low power cylindrical Hall thruster for nano-satellite “PROITERES-3” under development in Osaka Institute of Technology was designed, and the thruster performance was measured. As a result, a stable operation was achieved even with 10 W. The anode specific impulse and the anode thrust efficiency were 1570 s and 18.1%, respectively, with 66 W. Also, the discharge current oscillation was lower compared with that of SPT-type Hall thruster. |
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