Preliminary Investigation of Electromagnetic Thrust Characteristics in Electrodeless Compact Helicon Plasma Thruster
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概要
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In order to realize long-lived electric propulsion systems, we have been investigating an electrodeless plasma thruster. In our concept, high-density plasma from a compact helicon plasma source is accelerated by a magnetic nozzle for the thrust production. In order to optimize the thruster design, investigation of the thrust characteristics is needed. In this study, development of the electromagnetic thrust measurement system for compact helicon plasma thrusters and preliminary experiment of thrust measurement have been conducted. We have successfully developed a torsion-pendulum type thrust stand with measurement resolution of 10 μN. From the thrust measurement, the electromagnetic thrust increases with the Ar gas mass flow rate and plasma production power. The thrust force and the electron density jump are observed due to the discharge mode transition from the inductively coupled plasma to the helicon wave excited plasma. The electromagnetic thrust force is up to 340 μN (Ar gas mass flow rate of 1.0 mg/s, plasma production power of 400 W).
- THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCESの論文
著者
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Shinohara Shunjiro
Department Of Physics Faculty Of Science The University Of Tokyo
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Nakamura Takahiro
Department Of Allergy And Immunology National Research Institute For Child Health And Development Na
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Funaki Ikkoh
Institute Of Space And Astronautical Science Japan Aerospace Exploration Agency
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Tanikawa Takao
Research Institute Of Science And Technology Tokai University
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NISHIDA Hiroyuki
Deparment of Electrical Engineering, Hiroshima University
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FUNAKI Ikkoh
Institute of Space and Astronautical Science, JAXA
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HADA Tohru
Interdisciplinary Graduate School of Engineering Sciences, Kyushu University
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