Research and development of the pulsed plasma rocket engine system onboard osaka institute of technology micro artificial satellite

被引：0

作者：

Tahara H. ^{[1
]}

Naka M. ^{[1
]}

Takagi H. ^{[1
]}

Ikeda T. ^{[1
]}

Watanabe Y. ^{[2
]}

机构：

[1] Dept. of Mechanical Engineering, Osaka Institute of Technology, Asahi, Osaka 535-8585, 5-16-1, Omiya

[2] Graduate School of Engineering Science, Osaka University, Toyonaka 560-8531, 1-3, Machikaneyama

来源：

IEEJ Transactions on Fundamentals and Materials | 2010年 / 130卷 / 10期

关键词：

Electric propulsion; Electric rocket; Electrothermal acceleration; Micro artificial satellite; Powered flight; Pulsed plasma thruster;

D O I：

10.1541/ieejfms.130.851

中图分类号：

学科分类号：

摘要：

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. © 2010 The Institute of Electrical Engineers of Japan.

引用

页码：851 / 857

页数：6

共 13 条

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