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日本航空宇宙学会論文集
Vol. 65 (2017) No. 2 p. 82-86

記事言語:

http://doi.org/10.2322/jjsass.65.82

論文

A Hall thruster system for in-space propulsion has been developed as a part of a Japanese collaborative research and development project aiming at practical use of a high power anode layer type Hall thruster. Its thrust was measured at the ISAS/JAXA vacuum chamber facilities using a dual-pendulum thrust stand developed at the University of Tokyo. In the low specific impulse mode operation, thrust efficiency of 64% and thrust to power ratio of 80mN/kW were achieved. In the high specific impulse mode operation, the thruster was successfully operated at the acceleration voltage of up to 1,000V.

Copyright © 2017 The Japan Society for Aeronautical and Space Sciences

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