| Project/Area Number |
21860023
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| Research Category |
Grant-in-Aid for Research Activity Start-up
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Nagoya University (2010)
The University of Tokyo (2009) |
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Principal Investigator |
YOKOTA Shigeru Nagoya University, 工学研究科, 助教 (30545778)
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| Project Period (FY) |
2009 – 2010
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| Project Status |
Completed (Fiscal Year 2010)
|
| Budget Amount *help |
¥2,678,000 (Direct Cost: ¥2,060,000、Indirect Cost: ¥618,000)
Fiscal Year 2010: ¥1,274,000 (Direct Cost: ¥980,000、Indirect Cost: ¥294,000)
Fiscal Year 2009: ¥1,404,000 (Direct Cost: ¥1,080,000、Indirect Cost: ¥324,000)
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| Keywords | ホール型推進機 / 並列計算 / 宇宙推進工学 / 放電振動 / 電気推進機 |
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| Research Abstract |
A Hall thruster is one of the most promising electric propulsion systems. However this thruster has a serious problem : discharge oscillation. In our previous research, we found that the discharge is stabilized by propellant non-uniform feeding. In order to comprehend the mechanism of this method, we developed a numerical simulation code and observed the plasma in the thruster. As a result, we found that the stabilization was realized by the increment of the electron mobility in the thruster. However, this non-uniform feeding method decreases the thrust efficiency. This decrement of the efficiency is caused by two phenomena ; one is increment of the ion loss to the wall ; the other is increment of the electron current. In order to solve the first problem, we develop a wall guard made of an insulator. On the other hand, the 2^<nd> problem is difficult to solve because the electron current increases when the electron mobility increases. Therefore, we optimized a magnetic topology in the thruster in order that the electron mobility increases only in a part of the thruster. As a result, the discharge stabilization was realized without the decrement of the thrust efficiency.
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