| Project/Area Number |
07455389
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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 | UNIVERSITY OF TOKYO |
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Principal Investigator |
YOSHIHIRO Arakawa UNIV.OF TOKYO,FAC.OF ENG., PROFESSOR, 大学院・工学系研究科, 教授 (50134490)
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| Co-Investigator(Kenkyū-buntansha) |
OGIWARA Koji UNIV.OF TOKYO,FAC.OF ENG., RESEARCH ASSISTANT, 大学院・工学系研究科, 助手 (30092175)
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| Project Period (FY) |
1995 – 1996
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| Project Status |
Completed (Fiscal Year 1996)
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| Budget Amount *help |
¥7,500,000 (Direct Cost: ¥7,500,000)
Fiscal Year 1996: ¥1,000,000 (Direct Cost: ¥1,000,000)
Fiscal Year 1995: ¥6,500,000 (Direct Cost: ¥6,500,000)
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| Keywords | ELECTRIC PROPULSION / ARCJET / THRUSTER PEROFORMANCE / OPTICAL MEASUREMENT / HEATLOSS / ARC DISCHARGE / 比推力 |
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| Research Abstract |
The purpose of this research work is to investigate heat loss mechanisms in a DC arcjet by measuring heat loss flux from arc column to electrodes and electron temperature of the plasma with an optical measurement system and to improve thruster performance of the arcjet.
Using an segmented anode nozzle of the arcjet, heat loss distributions at the anode surface were investigated by measuring the temperature rise of cooling waters. To measure electron temperature distributions of the arc column, a high-resolution optical measurement system was designed and fabricated with a new CCD camera coupled with a monochrometer which had been used in the past experiment. With these experimental devices, we could obtain the above distributions and the relationship between the heat loss flux and electron temperature.
As a result, it was found that the heat loss flux to the anode nozzle can be reduced by lowering electron temperature and thermal conductivity of the arc column at the nozzle throat with a proper choice of operating and geometric design parameters such as propellant flow rate, discharge voltage, and nozzle shape.
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