@inproceedings{oai:jaxa.repo.nii.ac.jp:00016521,
 author = {三村, 大樹 and 梅田, 恭平 and 北園, 陽平 and 進藤, 崇央 and 青柳, 潤一郎 and 竹ヶ原, 春喜 and Mimura, Daiki and Umeda, Kyohei and Kitazono, Yohei and Shindo, Takahiro and Aoyagi, Junichiro and Takegahara, Haruki},
 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, We are working on research and development of rectangular PPT that is high specific impulse and coaxial PPT that is high impulse bit. Now, the propulsive performance of the thruster installed in the satellite is requested more widely following the extending the mission. A wide thrust performance was acquired and evaluated by changing the thruster size 0.5cm2 to 8.0cm2 at ablation area and changing the electric power of 3-75W as a thruster for the orbit control of 100kg class satellite in both a rectangular PPT and a coaxial PPT in the present study. It experimented at the high electric power to acquire a wide thrust performance and to evaluate the performance in this experiment. To acquire the operation result, carry out the continuous operation of 1,000,000shot at coaxial PPT. And to establish the stability operation condition, reduce the inductance of the entire system. At the result, continuous operation of 468,000shot was achieved on a coaxial PPT. And the stability operation condition on high electric power was established on a rectangular PPT., 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: AA0065073074},
 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 = {パルス型プラズマスラスタのスケーリング則および投入電力増加による推進性能評価実験},
 year = {2011}
}