Tokyo Metropolitan University
Tokyo Metropolitan University
Tokyo Metropolitan University
Tokyo Metropolitan University
Tokyo Metropolitan University
Tokyo Metropolitan University
出版者
宇宙航空研究開発機構宇宙科学研究所
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
雑誌名
平成22年度宇宙輸送シンポジウム: 講演集録
雑誌名(英)
Proceedings of Space Transportation Symposium: FY2010
Space Transportation FY2010 (January 20-21, 2011. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan
抄録（英）
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.
内容記述
形態: カラー図版あり
形態: CD-ROM1枚
内容記述（英）
Physical characteristics: Original contains color illustrations
Note: One CD-ROM
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
