| Project/Area Number |
15K14255
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| Research Category |
Grant-in-Aid for Challenging Exploratory Research
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| Allocation Type | Multi-year Fund |
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| Research Field |
Aerospace engineering
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| Research Institution | Kyushu Institute of Technology |
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Principal Investigator |
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| Co-Investigator(Kenkyū-buntansha) |
各務 聡 宮崎大学, 工学部, 准教授 (80415653)
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| Project Period (FY) |
2015-04-01 – 2018-03-31
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| Project Status |
Completed (Fiscal Year 2017)
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| Budget Amount *help |
¥3,900,000 (Direct Cost: ¥3,000,000、Indirect Cost: ¥900,000)
Fiscal Year 2017: ¥1,170,000 (Direct Cost: ¥900,000、Indirect Cost: ¥270,000)
Fiscal Year 2016: ¥1,170,000 (Direct Cost: ¥900,000、Indirect Cost: ¥270,000)
Fiscal Year 2015: ¥1,560,000 (Direct Cost: ¥1,200,000、Indirect Cost: ¥360,000)
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| Keywords | 小型推進機 / 固体推進剤 / 燃焼制御 / 非自燃性 / 酸化剤供給 / 小型化学推進機 / 酸化剤 |
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| Outline of Final Research Achievements |
In this research, we aimed at developing a small satellite thruster technology of a mechanism that enables ON-OFF included thrust control by supplying and adjusting the shortage of oxidizer component gas to fuel rich solid propellant by experiment and analysis. The test for fundamental phenomena using a strand combustor showed that the combustion rates were not much affected by N2O supply amount under the same combustion chamber pressure and N2O supply method, and that they increased with pressure rise like ordinary solid propellants. The test with a prototype thruster showed that the proposed concept is established, then that the corrected specific impulse was nearly 3/4 of the theoretical value, which was probabbly because of heat loss and the existence of wasted N2O not contributing to combustion reaction.
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