Research and Development of the Pulsed Plasma Rocket Engine System onboard Osaka Institute of Technology Micro Artificial Satellite
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- Tahara Hirokazu
- Dept. of Mechanical Engineering, Osaka Institute of Technology
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- Naka Masamichi
- Dept. of Mechanical Engineering, Osaka Institute of Technology
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- Takagi Hiroki
- Dept. of Mechanical Engineering, Osaka Institute of Technology
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- Ikeda Tomoyuki
- Dept. of Mechanical Engineering, Osaka Institute of Technology
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- Watanabe Yosuke
- Graduate School of Engineering Science, Osaka University
Bibliographic Information
- Other Title
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- 大阪工業大学・超小型人工衛星搭載用パルスプラズマロケットエンジンシステムの開発研究
- オオサカ コウギョウ ダイガク チョウコガタ ジンコウ エイセイ トウサイヨウ パルスプラズマロケットエンジン システム ノ カイハツ ケンキュウ
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Description
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 micro satellite with electrothermal pulsed plasma thrusters (PPTs) will be launched in 2010. The main mission is the first powered flight of micro satellite by electric thruster all over the world. This study aims at improvement in performance by changing configuration of PPTs. The total impulse of about 5 Ns was achieved with a teflon cylindrical discharge chamber 9.0 mm in length and 1.0 mm in diameter in 53,000-shot operation with 2.43 J/shot. Finally, the engineering model of PPT system was developed, and it is under operation as final test.
Journal
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- IEEJ Transactions on Fundamentals and Materials
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IEEJ Transactions on Fundamentals and Materials 130 (10), 851-857, 2010
The Institute of Electrical Engineers of Japan
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Details 詳細情報について
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- CRID
- 1390282679575613952
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- NII Article ID
- 10026693165
- 130000415278
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- NII Book ID
- AN10136312
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- ISSN
- 13475533
- 03854205
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- NDL BIB ID
- 10830582
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- Text Lang
- ja
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- Data Source
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- JaLC
- NDL
- Crossref
- CiNii Articles
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- Abstract License Flag
- Disallowed
