A Miniaturized Ion Thruster and Neutralizer With Microwave Discharge
- Paper number
IAC-05-C4.4.02
- Author
Mr. Tanisho Masahiko, Kyushu University, Japan
- Coauthor
Mr. Hiroshi Kataharada, Kyushu University, Japan
- Coauthor
Dr. Naoji Ymamoto, Kyushu University, Japan
- Year
2005
- Abstract
Several ion engines have been developed and used for artificial satellites on a geostationary orbit or planetary explorations. The demand for miniaturized propulsion system with low thrust, high specific impulse, high efficiency and continuous operation is growing because it is useful and attractive for main propulsion system of small satellite and precise attitude control of various size satellites. An ion engine is one of the electric propulsions and generates thrust by extracting ions in plasma with electrostatic grids. In the microwave discharge system, the propellant is ionized to produce plasma with accelerated electrons with electron cyclotron resonance heating. It will have longer lifetime and higher reliability compared to conventional DC discharge engines since it does not use thermionic cathode. In addition, a neutralizer plays an important role to prevent the satellite from charging up by neutralizing the ion beam. A miniature ion engine requires a miniature neutralizer. We have been developing a 18 mm-diameter microwave discharge ion engine and a 7 mm-diameter microwave discharge cylindrical neutralizer. At present as for this ion engine performance, the propellant utilization efficiency, the ion production cost and the thrust were 0.72, 770 V and 0.66 mN, respectively at input power of 8 W and Xe gas flow rate of 0.2 sccm. Its neutralizer is being designed for neutralizing the ion beam current of this engine. We will report on performances of both the engine and its neutralizer. Results described above will be presented.
- Abstract document
- Manuscript document
IAC-05-C4.4.02.pdf (🔒 authorized access only).
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