@inproceedings{oai:jaxa.repo.nii.ac.jp:00016514,
 author = {戸川, 和也 and 西田, 隆弘 and 杉本, 成 and 野瀬, 真 and 藤田, 剛 and 田原, 弘一 and Togawa, Kazuya and Nishida, Takahiro and Sugimoto, Naru and Nose, Makoto and Fujita, Tsuyoshi and Tahara, Hirokazu},
 book = {平成22年度宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium: FY2010},
 month = {},
 note = {平成22年度宇宙輸送シンポジウム(2011年1月20-21日. 宇宙航空研究開発機構宇宙科学研究所), 相模原市, 神奈川県, Space Transportation FY2010 (January 20-21, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Development of Hall thrusters for nano and low-power satellites below 100W is required. In lowering Hall thruster power, the cylindrical type Hall thruster is more advantage than conventional coaxialtype Hall thruster is more advantage than conventional coaxial-type Hall thruster. In this study, a very low-power cylindrical Hall thruster was designed, and the performance was measured. As a result, stable operation was achieved even with 10W. The specific impulse and the thrust efficiency are 1570sec and 18.1%, respectively, with 66W. Discharge current oscillation also increased by raising discharge voltage., 形態: カラー図版あり, 形態: CD-ROM1枚, Physical characteristics: Original contains color illustrations, Note: One CD-ROM, 資料番号: AA0065073067},
 publisher = {宇宙航空研究開発機構宇宙科学研究所, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)},
 title = {超小型衛星用シリンドリカル型ホールスラスタの開発研究},
 year = {2011}
}