Hall thruster development for Japanese space propulsion programs

Yushi Hamada; Junhwi Bak; Rei Kawashima; Hiroyuki Koizumi; Kimiya Komurasaki; Naoji Yamamoto; Yusuke Egawa; Ikkoh Funaki; Shigeyasu Iihara; Shinatora Cho; Kenichi Kubota; Hiroki Watanabe; Kenji Fuchigami; Yosuke Tashiro; Yuya Takahata; Tetsuo Kakuma; Yusuke Furukubo; Hirokazu Tahara

doi:10.2322/tjsass.60.320

Hall thruster development for Japanese space propulsion programs

Yushi Hamada, Junhwi Bak, Rei Kawashima, Hiroyuki Koizumi, Kimiya Komurasaki, Naoji Yamamoto, Yusuke Egawa, Ikkoh Funaki, Shigeyasu Iihara, Shinatora Cho, Kenichi Kubota, Hiroki Watanabe, Kenji Fuchigami, Yosuke Tashiro, Yuya Takahata, Tetsuo Kakuma, Yusuke Furukubo, Hirokazu Tahara

Research output: Contribution to journal › Article › peer-review

20 Citations (Scopus)

Abstract

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.

Original language	English
Pages (from-to)	320-326
Number of pages	7
Journal	Transactions of the Japan Society for Aeronautical and Space Sciences
Volume	60
Issue number	5
DOIs	https://doi.org/10.2322/tjsass.60.320
Publication status	Published - 2017
Externally published	Yes

Keywords

Hall Thruster
In-space Propulsion

ASJC Scopus subject areas

Aerospace Engineering
Space and Planetary Science

Access to Document

10.2322/tjsass.60.320

Cite this

Hamada, Y., Bak, J., Kawashima, R., Koizumi, H., Komurasaki, K., Yamamoto, N., Egawa, Y., Funaki, I., Iihara, S., Cho, S., Kubota, K., Watanabe, H., Fuchigami, K., Tashiro, Y., Takahata, Y., Kakuma, T., Furukubo, Y., & Tahara, H. (2017). Hall thruster development for Japanese space propulsion programs. Transactions of the Japan Society for Aeronautical and Space Sciences, 60(5), 320-326. https://doi.org/10.2322/tjsass.60.320

Hamada, Y, Bak, J, Kawashima, R, Koizumi, H, Komurasaki, K, Yamamoto, N, Egawa, Y, Funaki, I, Iihara, S, Cho, S, Kubota, K, Watanabe, H, Fuchigami, K, Tashiro, Y, Takahata, Y, Kakuma, T, Furukubo, Y & Tahara, H 2017, 'Hall thruster development for Japanese space propulsion programs', Transactions of the Japan Society for Aeronautical and Space Sciences, vol. 60, no. 5, pp. 320-326. https://doi.org/10.2322/tjsass.60.320

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abstract = "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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author = "Yushi Hamada and Junhwi Bak and Rei Kawashima and Hiroyuki Koizumi and Kimiya Komurasaki and Naoji Yamamoto and Yusuke Egawa and Ikkoh Funaki and Shigeyasu Iihara and Shinatora Cho and Kenichi Kubota and Hiroki Watanabe and Kenji Fuchigami and Yosuke Tashiro and Yuya Takahata and Tetsuo Kakuma and Yusuke Furukubo and Hirokazu Tahara",

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doi = "10.2322/tjsass.60.320",

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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

PY - 2017

Y1 - 2017

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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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Hall thruster development for Japanese space propulsion programs

Abstract

Keywords

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