Development of Integrated Fuel Cell Aboard Spacecraft, Operable under Ultra Low Temperature, Combined with Propulsion System
Project/Area Number |
19360388
|
Research Category |
Grant-in-Aid for Scientific Research (B)
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Allocation Type | Single-year Grants |
Section | 一般 |
Research Field |
Aerospace engineering
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Research Institution | Japan Aerospace Exploration Agency |
Principal Investigator |
KAWAGUCHI Junichiro Japan Aerospace Exploration Agency, 宇宙科学研究所, 教授 (10169691)
|
Co-Investigator(Kenkyū-buntansha) |
SONE Yoshitsugu 宇宙航空研究開発機構, 宇宙科学研究所, 准教授 (70373438)
HABU Hiroto 宇宙航空研究開発機構, 宇宙科学研究所, 助教 (60353421)
|
Project Period (FY) |
2007 – 2010
|
Project Status |
Completed (Fiscal Year 2010)
|
Budget Amount *help |
¥19,240,000 (Direct Cost: ¥14,800,000、Indirect Cost: ¥4,440,000)
Fiscal Year 2010: ¥4,940,000 (Direct Cost: ¥3,800,000、Indirect Cost: ¥1,140,000)
Fiscal Year 2009: ¥4,940,000 (Direct Cost: ¥3,800,000、Indirect Cost: ¥1,140,000)
Fiscal Year 2008: ¥4,420,000 (Direct Cost: ¥3,400,000、Indirect Cost: ¥1,020,000)
Fiscal Year 2007: ¥4,940,000 (Direct Cost: ¥3,800,000、Indirect Cost: ¥1,140,000)
|
Keywords | 燃料電池 / 統合型 / 推進機関 / 触媒 / 宇宙機 |
Research Abstract |
The hydrazine based freeze-resistant liquid propellants were studied in the effort to decrease the dry mass of the propulsion system for spacecraft. This research is also related to the integration between the propulsion system and the fuel cell electrical power supply system which adopts the same combination of fuel and oxidizer. The temperature control device is usually equipped to preserve hydrazine in liquid phase because of its freezing point of approximately 275K. Lowering of the freezing point of hypergolic propellants will contribute to the minimization of the mass for the propulsion system. A hydroxylamine water solution was suggested as a candidate in this research. Hydroxylamine has a high chemical potential and is also a carbon-free material. Based on the above results, the fuel cell reaction was tested. First, the fuel with the m.p. less than -40℃ was prepared, and the fuel was electrochemically reacted with oxidant. From the results, We confirmed that the fuel could be used for the fuel cell.
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Report
(6 results)
Research Products
(3 results)
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[Presentation] 守宙探査機角耐侮温推進剤の研究2011
Author(s)
羽生宏人, 曽根理嗣, 高見剛史, 川口淳一郎
Organizer
日本航空宇宙学会/航空原動機宇雷推進講演会
Place of Presentation
広島県広島YMCAホール
Year and Date
2011-03-03
Related Report
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