2013 Fiscal Year Final Research Report
Innovative Miniature Propulsion System using Low-Power, Microwave Discharge Ion Thruster
| Project/Area Number |
22686080
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| Research Category |
Grant-in-Aid for Young Scientists (A)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | The University of Tokyo |
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Principal Investigator |
KOIZUMI Hiroyuki 東京大学, 先端科学技術研究センター, 准教授 (40361505)
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| Project Period (FY) |
2010-04-01 – 2014-03-31
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| Keywords | イオンスラスタ / プラズマ / 小型衛星 / イオンエンジン / 小型イオン推進システム / マイクロスラスタ |
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| Research Abstract |
These days, small satellites (less than 100 kg) are innovating the space utilization and development and one of the key technologies is the development of high-performance, small propulsion system using ion thrusters. The purpose of this study is to realize such advanced small propulsion systems and various subjects were conducted to understand the microwave discharge plasma (microwave transmission and plasma density profile), to clarify the characteristics of the thruster (plume, thrust, and thrust noise), and to verify the propulsion system (long time operation and BBM of gas system). The conclusions of these studies were utilized to design and develop the MIPS (miniature ion propulsion system) which was installed on a 50-kg, small satellite, Hodoyoshi-4.
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[Journal Article] Electric field measurement in microwave discharge ion thruster with electro-optic probe2013
Author(s)
Ise, T., Tsukizaki, R., Togo, H., Koizumi, H., and Kuninaka, H.
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Journal Title
Rev. Sci. Instrum.
Volume: Volume 83, No.124702
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