2004 Fiscal Year Final Research Report Summary
Research and Development of Advanced High-Density Helicon Plasma Source for Plasma Rocket Engine
| Project/Area Number |
14350514
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| Research Category |
Grant-in-Aid for Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | National University Corporation Tokyo University of Agriculture and Technology (2004)
Institute of Space and Astronautical Science (2002-2003) |
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Principal Investigator |
TOKI Kyoichiro National University Corporation Tokyo University of Agriculture and Technology, Graduate School of Institute of Symbiotic Science and Technology, Professor, 大学院・共生科学技術研究部, 教授 (40172142)
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| Co-Investigator(Kenkyū-buntansha) |
SHINOHARA Shunjiro National University Corporation Kyushu University, Interdisciplinary Graduate School of Engineering Sciences, Associate Professor, 大学院・総合理工学研究院, 助教授 (10134446)
TANIKAWA Takao Tokai University, Research Institute of Science and Technology, Professor, 総合科学技術研究所, 教授 (70207174)
KUNINAKA Hitoshi Independent Administrative Agency Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Professor, 宇宙科学研究本部・宇宙輸送工学研究系, 教授 (60234465)
NISHIYAMA Kazutaka Independent Administrative Agency Japan Aerospace Exploration Agency, Institute of Space and Astronautical Science, Research Associate, 宇宙科学研究本部・宇宙輸送工学研究系, 助手 (60342622)
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| Project Period (FY) |
2002 – 2004
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| Keywords | Plasma Rocket Engine / Helicon / Plasma Source |
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| Research Abstract |
In this research, we investigated an electrodeless plasma source producing and accelerating high-density plasma for Plasma Rocket Engine. Several RF antennae were examined to produce electrodeless discharge plasmas. A saddle-type antenna showed superior ignition characteristics around 40-60 MHz under only 10 W RF input power. A few working gases were tested and mono-atomic Argon was selected for the sake of easy analysis. The plasma was initiated inside a glass tube with 2.5 cm i.d. and 80 cm length which was one of the world smallest helicon source. The flow rate was 1 mg/s(34 sccm). The plasma seemed to be inductively coupled when the RF input power was less than 50 W, but beyond 200 W very dense plasma over 10^<12> cm^<-3> was produced. At that time, 2 x 10^<12> cm^<-3> density was attained under the applied magnetic field up to 200 G. Judging from its abrupt increase of density, disappearing without applied fields and the necessary conditions analytically predicted by Shamrai, our overseas research collaborator, this was recognized as a helicon jump.
The world largest volume helicon plasma over 5 x 10^<12> cm^<-3> density was successfully produced in a large magnetized plasma device (74 cm id.,486 cm length, Bmax=2 kG) with a 42 cm diam. 4-turn antenna, using a maximum power of 4 kW pulsed RF amplifier. The method controling radial plasma density distribution was found by adjusting the excitation antenna pattern and the applied field distribution.
On the other hand as for the acceleration mechanisms, we newly proposed 2 kinds of electrodeless methods. One is to induce a azimuth current inside the plasma by coil antenna and make step-by-step pulsed electromagnetic acceleration. The other is to continuously accelerate plasma by the penetration of rotating electric field applied. Both methods were analytically found to be feasible.
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[Book] 電気推進ロケット入門2003
Author(s)
栗木恭一, 他(執筆分担)
Total Pages
258
Publisher
東京大学出版会
Description
「研究成果報告書概要(和文)」より
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