TY - JOUR
T1 - Hall thruster development for Japanese space propulsion programs
AU - Hamada, Yushi
AU - Bak, Junhwi
AU - Kawashima, Rei
AU - Koizumi, Hiroyuki
AU - Komurasaki, Kimiya
AU - Yamamoto, Naoji
AU - Egawa, Yusuke
AU - Funaki, Ikkoh
AU - Iihara, Shigeyasu
AU - Cho, Shinatora
AU - Kubota, Kenichi
AU - Watanabe, Hiroki
AU - Fuchigami, Kenji
AU - Tashiro, Yosuke
AU - Takahata, Yuya
AU - Kakuma, Tetsuo
AU - Furukubo, Yusuke
AU - Tahara, Hirokazu
N1 - Funding Information:
The authors gratefully acknowledge support from JAXA, IA and IHI. Research results were obtained using the ion engine endurance test facility at ISAS, JAXA. The contributions of Prof. Hitoshi Kuninaka, Prof. Kazutaka Nishiyama, Prof. Satoshi Hosoda, Prof. Ryudo Tsukizaki, and their staff are greatly appreciated. For the experiment at GIT, the contributions of Prof. Mitchell Walker and his staff are much appreciated.
Publisher Copyright:
© 2017 The Japan Society for Aeronautical and Space Sciences
PY - 2017
Y1 - 2017
N2 - Three different types of high power Hall thrusters—anode layer type, magnetic layer type with high specific impulse, and magnetic layer type with dual mode operation (high thrust mode and high specific impulse mode)—have been developed, and the thrust performance of each thruster has been evaluated. The thrust of the anode layer type thruster is in the range of 19–219 mN, with power in the range of 325–4500 W. The thrust of the high specific impulse magnetic layer type thruster was 102 mN, with specific impulse of 3300 s. The thrust of the bimodal operation magnetic layer thruster was 385 mN with specific impulse of 1200 s, and 300 mN with specific impulse of 2330 s. The performance of these thrusters demonstrates that the Japanese electric propulsion community has the capability to develop a thruster for commercial use.
AB - Three different types of high power Hall thrusters—anode layer type, magnetic layer type with high specific impulse, and magnetic layer type with dual mode operation (high thrust mode and high specific impulse mode)—have been developed, and the thrust performance of each thruster has been evaluated. The thrust of the anode layer type thruster is in the range of 19–219 mN, with power in the range of 325–4500 W. The thrust of the high specific impulse magnetic layer type thruster was 102 mN, with specific impulse of 3300 s. The thrust of the bimodal operation magnetic layer thruster was 385 mN with specific impulse of 1200 s, and 300 mN with specific impulse of 2330 s. The performance of these thrusters demonstrates that the Japanese electric propulsion community has the capability to develop a thruster for commercial use.
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U2 - 10.2322/tjsass.60.320
DO - 10.2322/tjsass.60.320
M3 - Article
AN - SCOPUS:85028943791
VL - 60
SP - 320
EP - 326
JO - Transactions of the Japan Society for Aeronautical and Space Sciences
JF - Transactions of the Japan Society for Aeronautical and Space Sciences
SN - 0549-3811
IS - 5
ER -