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

研究成果: Article査読

18 被引用数 (Scopus)

抄録

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.

本文言語English
ページ(範囲)320-326
ページ数7
ジャーナルTransactions of the Japan Society for Aeronautical and Space Sciences
60
5
DOI
出版ステータスPublished - 2017
外部発表はい

ASJC Scopus subject areas

  • 航空宇宙工学
  • 宇宙惑星科学

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