論文 - 増井　博一

Antenna configuration effects on thrust performance of miniature microwave discharge ion engine 査読有り

Yamamoto N., Masui H., Kataharada H., Nakashima H., Takao Y.

Journal of Propulsion and Power   22 ( 4 )   925 - 928   2006年07月

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記述言語：英語   掲載種別：研究論文（学術雑誌）

The effects of antenna configuration on the thrust performance of a 30-W-class miniature microwave discharge ion engine were investigated. The ion beam currents were measured for three different antenna configurations such as disc, star, and cross antennas. The ion beam current of the star antenna was the largest among the three configurations and that of the disc antenna was the smallest. The effect of good coupling with plasma exceeded the effect of large losses on the antenna surface under low mass flow rate with low plasma density. The effect of large losses on the antenna surface also exceeded the effect of good coupling with plasma under high mass flow rate. The results showed that the optimum antenna shape depends on the desired mass flow level due to the tradeoff between microwave plasma coupling efficiency and surface-area recombination. It was also found that the disc antenna was the best at low mass flow rate and the star antenna was the best at high mass flow rate.

DOI： 10.2514/1.18833

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Antenna Configuration Effects on Thrust Performance of Miniature Microwave Discharge Ion Engine 査読有り

N. Yamamoto, H. Masui, H. Kataharada, Y. Takao and H. Nakashima

Journal of Propulsion and Power   2006年06月

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記述言語：英語   掲載種別：研究論文（学術雑誌）

Numerical analysis of microwave ion engine using electromagnetic particle code 査読有り

Masui H., Tanoue T., Nakashima H., Funaki I.

Thin Solid Films   506-507   609 - 612   2006年05月

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記述言語：英語   掲載種別：研究論文（学術雑誌）

A simulation code has been developed for analyzing plasma behavior and microwave propagation in a microwave ion engine. The code consists of PIC (particle-in-cell) method and FDTD (finite-difference-time-domain) method. In the present study, 10-cm-class microwave ion engine developed by the Japan Aerospace Exploration Agency (JAXA) is adopted as a calculation model. The microwave propagations in the discharge chamber are compared under boundary conditions such as absorption and reflection. In the calculation with plasma, effect of boundary condition on electron energy is investigated. As a result, it is found that increase of electron energy is larger for reflection boundary condition than absorption one. © 2005 Elsevier B.V. All rights reserved.

DOI： 10.1016/j.tsf.2005.08.046

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Numerical Analysis of Microwave Ion Engine Using Electromagnetic Particle Code 査読有り

H.Masui, Y. Tashiro, N. Yamamoto, H. Nakashima and I. Funaki

Thin Solid Films   2006年05月

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担当区分：責任著者   記述言語：英語   掲載種別：研究論文（学術雑誌）

Electromagnetic field analysis for microwave discharge ion engine using multi mono-poles antenna system 査読有り

Izumi K., Masui H., Shinyashiki K., Yamamoto N., Nakashima H.

International Astronautical Federation - 56th International Astronautical Congress 2005   7   4703 - 4707   2005年12月

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記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）

We report here on an optimal configuration of antennas using multi mono-pole systems. In order to optimize the position and length of antenna, the transmission efficiency are analyzed by finite difference time domain (FDTD) method, which is known for its usefulness and simplicity to calculate to electromagnetic field. The relation between the antenna length and transmission efficiency was investigated. First this report shows that experimental data up to now. Then the microwave transmission is calculated by using poynting vector. When transmission value of microwave is calculated, we varied the parameters such as antenna length, yoke length and number of antennas respectively. Finally, we obtain on guiding design principle of ion engines by comparing experimental data and numerical calculation conclusions.

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Development of small-scale microwave discharge ion thruster 査読有り

Takao Y., Masui H., Miyamoto T., Kataharada H., Ijiri H., Nakashima H.

Vacuum   73 ( 3-4 )   449 - 454   2004年04月

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記述言語：英語   掲載種別：研究論文（国際会議プロシーディングス）

Study of a small-scale ion engine (diameter of 2.5 cm, input microwave power up to 25 W) utilizing microwave-discharged plasma for space propulsion is reported. The ion extraction tests are conducted under several conditions such as the input microwave power range of 15-25 W, the Ar gas (as propellant) flow rate range of 1.5-3.5 sccm, and two types of antenna shape (L-type or disk antenna). In the tests, ion beam currents and distributions of ion beam current density are measured. As a result, maximum ion current of 8.2 mA is attained at input power of 25 W and Ar gas flow rate of 3.15 sccm with the L-type antenna. Ion production cost and propellant utilization efficiency are estimated from the ion current measurements to examine performances of the thruster. The plasma parameter measurements of electron temperature and density in the plasma source are also carried out. © 2004 Elsevier Ltd. All rights reserved.

DOI： 10.1016/j.vacuum.2003.12.066

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