| Project/Area Number |
03452096
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| Research Category |
Grant-in-Aid for General Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | UNIVERSITY OF TOKYO |
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Principal Investigator |
ARAKAWA Yoshihiro UNIV.OF TOKYO, FAC.OF ENG.PROFESSOR, 工学部, 教授 (50134490)
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| Co-Investigator(Kenkyū-buntansha) |
KOBAYASHI Tsuruo UNIV.OF TOKYO, FAC.OF ENG.RESEARCH ASSISTANT, 工学部, 助手 (90215343)
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| Project Period (FY) |
1991 – 1993
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| Project Status |
Completed (Fiscal Year 1993)
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| Budget Amount *help |
¥6,200,000 (Direct Cost: ¥6,200,000)
Fiscal Year 1993: ¥1,300,000 (Direct Cost: ¥1,300,000)
Fiscal Year 1992: ¥2,000,000 (Direct Cost: ¥2,000,000)
Fiscal Year 1991: ¥2,900,000 (Direct Cost: ¥2,900,000)
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| Keywords | THRUSTER / PERFORMANCE / PLASMA / ELECTRIC PROPULSION / HALL CURRENT / HOLLOW CATHODE / ROCKET / ホールスラスタ / 推進性能 / ホ-ルスラスタ / 電磁加速 |
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| Research Abstract |
A magnetic circuit that largely influences Hall thruster performance was designed by using two-dimensional FEM magnetic analysis code which was developed previously. A solenoidal coil was positioned at the center of acceleration channel in order to have high radial magnetic fields applied on it.
Based on the above circuit design, the acceleration channel of a thruster was designed and fabricated. In addition, power supplies for plasma production, ion acceleration, and neutralization were ordered and assembled.
The thruster was operated in the vacuum system which consists of a 0.8 m diam. and 2.5 m long chamber and 10,000 1/s pumping system. We obtained stable arc discharge as well as normal plasma production and ion beam extraction. Also, discharge voltage-current characteristics were examined and show a general tendency for this kind of thruster.
Increasing an input power up to 1.5kW, thrust measurement was done to estimate thruster performance. Ion beam current was also measured to obtain acceleration efficiency and to investigate the effect of channel geometry, field strength, and operating conditions on it.
A hollow cathode was installed on the thruster in place of a filament cathode. With the hollow cathode, a maximum thrust efficiency of 34 % was obtained when xenon gas was used as the propellant.
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