| 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 |
搭載用水サイクル宇宙推進システムの検討 |
| 言語 |
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言語 |
jpn |
| キーワード |
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主題Scheme |
Other |
|
主題 |
宇宙機推進 |
| キーワード |
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主題Scheme |
Other |
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主題 |
水サイクル |
| キーワード |
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主題Scheme |
Other |
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主題 |
有人軌道実験室 |
| キーワード |
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主題Scheme |
Other |
|
主題 |
JEM |
| キーワード |
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主題Scheme |
Other |
|
主題 |
宇宙飛行試験 |
| キーワード |
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主題Scheme |
Other |
|
主題 |
燃料電池 |
| キーワード |
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主題Scheme |
Other |
|
主題 |
電力供給 |
| キーワード |
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主題Scheme |
Other |
|
主題 |
電気分解 |
| 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 |
spacecraft 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 |
water cycle |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
|
主題 |
manned orbital laboratory |
| 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 |
JEM |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
|
主題 |
space flight test |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
|
主題 |
fuel cell |
| キーワード |
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言語 |
en |
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主題Scheme |
Other |
|
主題 |
electric power supply |
| キーワード |
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言語 |
en |
|
主題Scheme |
Other |
|
主題 |
electrolysis |
| 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 |
|
資源タイプ |
conference paper |
| アクセス権 |
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|
アクセス権 |
metadata only access |
|
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 |
A study of flight test-bed for water cycle space propulsion system |
| 著者 |
都木, 恭一郎
橋本, 保成
藤田, 孝
石井, 忠司
Toki, Kyoichiro
Hashimoto, Yasunari
Fujita, Takashi
Ishii, Tadashi
|
| 著者所属 |
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宇宙航空研究開発機構 宇宙科学研究本部 |
| 著者所属 |
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宇宙航空研究開発機構 宇宙科学研究本部 |
| 著者所属 |
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AEC藤田 |
| 著者所属 |
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次世代技術 |
| 著者所属（英） |
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en |
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Japan Aerospace Exploration Agency Institute of Space and Astronautical Science |
| 著者所属（英） |
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|
en |
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Japan Aerospace Exploration Agency Institute of Space and Astronautical Science |
| 著者所属（英） |
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|
en |
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Advanced Engineering Consulting Fujita |
| 著者所属（英） |
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|
en |
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Jisedaitech L. P. |
| 出版者 |
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出版者 |
宇宙航空研究開発機構宇宙科学研究本部 |
| 出版者（英） |
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出版者 |
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS) |
| 書誌情報 |
第23回宇宙エネルギーシンポジウム 平成15年度
en : The 23rd ISAS Space Energy Symposium March 9, 2004
p. 74-78,
発行日 2004-06
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| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
A water cycle space propulsion system has been studied for a space flight test onboard the space station Japanese Experimental Module KIBOU. The water cycle space propulsion system is characterized as a clean, safe and non-toxic system being friendly to the personnel, because the power source is based upon the solar energy in space and the water is the working fluid on the ground. In the future, the water cycle can be merged into a life support system in space as well as the propulsion and power system. This test bed on the KIBOU will provide a 250 W water electrolysis capability and the corresponding power for fuel cell as its reverse cycle. During the sunshine, the water electrolysis process is activated for 45 min of half a revolution around the earth, and the rest of the revolution during the sunshade is dedicated for a propulsion experiment using GH2/GO2 and a fuel cell experiment. The expected installation is on a pallet-type bus structure interface with a deployable exclusive solar array for this experiment and other common interfaces to the exposed facility of KIBOU. Presently, some basic experiments were finished on the ground for a single reversible cell at a room temperature environment. The fuel cell mode provides 0.1 A/sq cm current density at output voltage of 0.6 V while the water electrolysis mode provides 0.5 g/h throughput at 0.3 W/sq cm. All the water cycle system is placed on a 2-axis rotatable circular plate which can change the gravitational direction to the system so as to apply +/- 1 G. On the other hand, the ignition capability of GH2/GO2 has been greatly improved using a catalytic combustion method at the upstream of the main combustion chamber where the secondary GH2 is injected. So-called an ignition delay has been completely eliminated from the present ignition experiments. The water cycle space propulsion system will be composed of a 2 N GH2/GO2 thruster and two cells. One is used for fuel cell and the other is for electrolysis. The water filling/drain, if adopted a single cell configuration, is very much troublesome process. The pressurization of both 16 litter H2 and 8 litter O2 gaseous tanks should be limited less than 7 MPa because of the safety requirement for pressure vessels. The water tank is 4 litter. To prevent inadvertent mechanical disturbances to the ISS, the generated two thrusts are aligned to the opposite direction. The thrusting period is about 6 seconds per one revolution around the earth. |
| 資料番号 |
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内容記述タイプ |
Other |
|
内容記述 |
資料番号: AA0047275016 |
