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- YAMAMOTO Naoji
- Department of Advanced Energy Engineering Science, Kyushu University
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- TAKASE Kohei
- Department of Advanced Energy Engineering Science, Kyushu University
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- HIRANO Yuya
- Department of Aeronautics and Astronautics, The University of Tokyo
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- KOMURASAKI Kimiya
- Department of Aeronautics and Astronautics, The University of Tokyo
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- KAKAMI Akira
- Department of Mechanical Engineering, University of Miyazaki
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- TSUKIZAKI Ryudo
- Institute of Space and Astronautical Science, JAXA
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- HOSODA Satoshi
- Institute of Space and Astronautical Science, JAXA
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- KUNINAKA Hitoshi
- Institute of Space and Astronautical Science, JAXA
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- YOKOTA Shigeru
- Space Exploration Engineering Division, University of Tsukuba
抄録
<p>As a part of a Japanese collaborative research and development project on practical use of a high power anode layer type Hall thruster, a 5 kW class anode layer Hall thruster (RAIJIN94) has been developed and the thrust performance has been evaluated. The thrust was measured in the ion engine endurance test facility at ISAS/JAXA using a pendulum thrust stand developed at the University of Tokyo. The thrust performance at 3 kW operation was measured (xenon anode mass flow rate of 9.8 mg/s and xenon cathode mass flow rate of 0.5 mg/s); the thrust, specific impulse, and thrust efficiency were found to be 160 mN, 1600 sec and 0.42, respectively. The thrust performance depends on magnetic field configuration, that is, the strength of the magnetic field and the ratio of trim coil to inner/outer coil.</p>
収録刊行物
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 14 (ists30), Pb_183-Pb_187, 2016
一般社団法人 日本航空宇宙学会
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詳細情報
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- CRID
- 1390001205320755840
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- NII論文ID
- 130005331201
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- ISSN
- 18840485
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- Crossref
- CiNii Articles
- KAKEN
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- 抄録ライセンスフラグ
- 使用不可