| Item type |
会議発表論文 / Conference Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
マイクロ波放電式イオンエンジンファミリーの研究開発とその応用展開 |
| 言語 |
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言語 |
jpn |
| キーワード |
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主題Scheme |
Other |
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主題 |
マイクロ波放電イオンエンジン |
| キーワード |
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主題Scheme |
Other |
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主題 |
電気推進 |
| キーワード |
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主題Scheme |
Other |
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主題 |
MUSES-C宇宙機 |
| キーワード |
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主題Scheme |
Other |
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主題 |
宇宙技術 |
| キーワード |
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主題Scheme |
Other |
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主題 |
宇宙探査 |
| キーワード |
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主題Scheme |
Other |
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主題 |
プラズマ発生器 |
| キーワード |
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主題Scheme |
Other |
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主題 |
寿命 |
| キーワード |
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主題Scheme |
Other |
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主題 |
C/C化合物 |
| キーワード |
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主題Scheme |
Other |
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主題 |
深宇宙 |
| キーワード |
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主題Scheme |
Other |
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主題 |
研究開発 |
| キーワード |
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主題Scheme |
Other |
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主題 |
高エネルギー中性原子 |
| キーワード |
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主題Scheme |
Other |
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主題 |
エネルギー消費 |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
microwave discharge ion engine |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
electric propulsion |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
MUSES-C spacecraft |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
aerospace technology |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
space exploration |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
plasma generator |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
life time |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
C/C composite |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
deep space |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
research and development |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
energetic neutral atom |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
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主題 |
energy consumption |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_5794 |
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資源タイプ |
conference paper |
| アクセス権 |
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アクセス権 |
metadata only access |
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アクセス権URI |
http://purl.org/coar/access_right/c_14cb |
| その他のタイトル（英） |
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その他のタイトル |
R & D of microwave discharge ion engine family and its application |
| 著者 |
國中, 均
都木, 恭一郎
清水, 幸夫
西山, 和孝
Kuninaka, Hitoshi
Toki, Kyoichiro
Shimizu, Yukio
Nishiyama, Kazutaka
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| 著者所属 |
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宇宙科学研究所 |
| 著者所属 |
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宇宙科学研究所 |
| 著者所属 |
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宇宙科学研究所 |
| 著者所属 |
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宇宙科学研究所 |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science |
| 著者所属（英） |
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en |
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Institute of Space and Astronautical Science |
| 出版者 |
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出版者 |
宇宙科学研究所 |
| 出版者（英） |
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出版者 |
The Institute of Space and Astronautical Science (ISAS) |
| 書誌情報 |
第22回宇宙エネルギーシンポジウム 平成14年度
en : The 22nd ISAS Space Energy Symposium March 12, 2003
p. 91-95,
発行日 2003-05
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
Institute of Space and Astronautical Science (ISAS) has just manufactured the MUSES-C spacecraft for the flight operation in May this year. That space mission aims to retrieve specimen from one of the asteroids to Earth. The round trip will be executed by four sets of the Microwave Discharge Ion Engine mu10. MUSES-C reveals that even the medium class launch rockets M-V combined with the electric propulsion (EP) enables the deep space exploration. The mu10 has been developed since 1988. In those days the launch capability and the weight penalty of EP prevented from application of EP to the scientific space mission. However, the needs for the deep space exploration, the extension of space technology and the spirits of the EP engineers realize the mu10, of which the technology is 'the foothold in deep space' and should be refined continuously. The mu10 generates 8.5 mN thrust force at 3,000 sec specific impulse with 350 W electric power consumption. Main feature of mu10 is the plasma generation by microwave without electrodes, which are one of the life critical components. Not only the main plasma source but also the neutralizer is driven by the microwave power. Another feature is application of carbon-carbon composite material to the electro-static acceleration grids. Twice endurance tests proved the long life of mu10 over 20,000 hours. The R&D efforts devote to develop mu20 and mu10HIsp. The mu20 has a capability of 27 mN thrust force with 900 W power consumption using a grid system of 20 cm diameter. Its thrust power ratio will be improved 30 mN/kW in comparison with 22 mN/kW of mu10. The technological key to achieve the high thrust power ratio is the plasma generation with low ion production cost. The optimized design to arrange the magnetic track in the plasma source and the microwave feeder attained the ion production cost less than 200 eV. High capacity neutralizer was also developed based on the technology of mu10. It can emit the electron current over 500 mA at less than 40 V contact voltage. Another R&D program is mu10HIsp, which generated 27 mN thrust force of 10,000 sec specific impulse with 2.5 kW power. It will use the plasma source and the neutralizer identical to the mu10. On the other hand the electro-static grid and the DC block are newly under development. The electric powers of mu10, mu20 and mu10HIsp are 350 W, 900 W and 2.5 kW, and the specific impulse 3,000 sec, 2,800 sec and 10,000 sec, thrust force 8.5 mN, 27 mN and 27 mN. The family of the microwave discharge ion engine mu-series will contribute the space mission including the air drag compensation and the formation flight in LEO as well as the round trip exploration and the Jupiter probe in the deep space. It has just been started to research the probing of the high altitude atmosphere. The plasma beam exhausted from the ion engine causes the charge separation so as to behave as an ion with high energy in the far field from the origin. The ion flights along the geo-magnetic line rotating as the gyro-motion and collides with the atmosphere as the results that it loses the electric charge and move straight forward regardless the magnetic and electric field. These generated particles are called the energetic neutral atoms (ENA). If ENA can be detected and analyzed the earth atmosphere might be able to be remote-sensed. The location to happen the charge exchange collision will be recognized on the basis of the flight direction of ENA and the time delay between the plasma beam emission and the ENA detection. The count rate and energy loss of ENA are reflected to the density and species of atmosphere, respectively. The natural ENA originated from the solar wind and the ring current is observed by the IMAGE satellite launched in March 2000. The artificial ENA originated from the ion engine is the subject of the research. The family of the microwave discharge ion engine will be applied to not only the space mission but also the non-propulsion field. |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: AA0045915019 |
