Electric Propulsion, Pulsed Plasma Thruster, Nano Satellite, Powered Flight
その他のタイトル（英）
Performance Prediction of Electrothermal Pulsed Plasma Thrusters for the 1st and 2nd Osaka Institute of Technology PROITERES Satellites by Numerical Calculation
Osaka Institute of Technology
Osaka Institute of Technology
Osaka Institute of Technology
Osaka Institute of Technology
Osaka Institute of Technology
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出版者
宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
雑誌名
平成24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: FY2012
Space Transportation FY2012 (January 17-18, 2013. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan
抄録（英）
The Project of Osaka-Institute-of-Technology Electric-Rocket-Engine onboard Small Space Ship (PROITERES) was started at Osaka Institute of Technology in 2007. In PROITERES, a 14.5-kg nano satellite with electrothermal pulsed plasma thrusters (PPT) was launched on September 9th 2012. The main mission is powered flight of nano satellite by electric thruster itself. Now, we will be trying to establish a contact to satellite. After establishing satellite ignitions by command the thruster will be operated from the ground. In this paper, the performance is predicted by numerical simulation and ground experiment. Furthermore, the 2nd PROITERES satellite with high-power PPT systems was introduced.
内容記述
形態: カラー図版あり
形態: PDF
内容記述（英）
Physical characteristics: Original contains color illustrations
Physical characteristics: PDF
数値計算による大阪工業大学プロイテレス衛星1、2号機搭載電熱加速型パルスプラズマスラスタの性能予測
61856156.pdf
(546.93KB)
