Improvement of Microwave Discharge Ion Engine with Antenna for Uniform and High dense Plasma Generation
Improvement of Microwave Discharge Ion Engine with Antenna for Uniform and High dense Plasma Generation
批准号:
16560691
负责人:
NAKASHIMA Hideki
金额:
$2.3万
依托单位:
依托单位国家:
日本
项目类别:
Grant-in-Aid for Scientific Research (C)
财政年份:
2004
资助国家:
日本
项目状态:
已结题
起止时间:
2004 至 2006
中文摘要
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英文摘要
The aim of this study is developing a novel microwave discharge ion thruster, uniform plasma generation and high thrust density in cooperation with Japan Aerospace Exploration Agency.Numerical simulation was done in order to optimize the engine configurations for developing two size ion engines. We have developed a code coupling particle-in-cell (PIC) method and finite difference time domain (FDTD) one. Adopting these methods has advantages in that PIC method can treat collision process and distribution function while FDTD method can analyze absorption of microwave in plasma.The following conclusions were obtained.1) With respect to microwaves propagation, the dependence of antenna configuration on microwave propagation efficiency was proved, this led the optimum antenna configuration.2) With respect to the plasma production in the discharge chamber, electrons existing between the yokes are energized from the ECR and the electric field of high strength near the antenna, and the plasma is maintained by ionization collisions of the energized electrons.3) the antenna needs to be close to the ECR region for the effective plasma production.Applying the design law from numerical analysis, novel 100 mm class ion engine was developed and the thrust performance of it was measured. The thruster performance of this engine, propellant utilization, ion beam production cost, are 0.62,276 W/A, respectively, at mass flow rate =0.24 mg/s, and incident microwave power = 32 W.On the basis of numerical simulation results and experimental results of 100 mm class ion engine, a miniature microwave discharge ion engine was developed. The thruster performance of the miniature ion engine, propellant utilization, ion beam production cost, estimated thrust, estimated specific impulse and estimated thrust efficiency are 0.92,590 W/A,0.80 mN,4,180 sec and 0.58,respectively, at mass flow rate =0.020 mg/s, and incident microwave power = 10 W.
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A Miniaturized Ion Thruster and Neutralizer with Microwave Discharge
微波放电小型化离子推进器和中和器
DOI:
--
发表时间:
2005
期刊:
56^<th> Int.Astronautical Congress, IAC-05-CIAC-05-C4.4.02
影响因子:
--
作者:
[N.Yamamoto, et al., N.Yamamoto, K.Izumi, M.Tanisho]
通讯作者:
M.Tanisho
Electromagnetic Field Analysis for Microwave Discharge Ion Engine using Multi-monopole Antenna System
使用多单极天线系统的微波放电离子发动机电磁场分析
DOI:
--
发表时间:
2005
期刊:
56^<th> Int.Astronautical Congress, IAC-05-CIAC-05-C4.P.03
影响因子:
--
作者:
[N.Yamamoto, et al., N.Yamamoto, K.Izumi]
通讯作者:
K.Izumi
DOI:
--
发表时间:
2005
期刊:
Proc.29^<th> Int.Electric Propulsion Conference, IEPC-2005-055
影响因子:
--
作者:
[N.Yamamoto, et al., N.Yamamoto, K.Izumi, M.Tanisho, 中山宜典, K.Nishiyama]
通讯作者:
K.Nishiyama
Development of a New Microwave Discharge Type Ion Engine
新型微波放电式离子发动机的研制
DOI:
--
发表时间:
2004
期刊:
Vacuum Vol.73, No.3-4
影响因子:
--
作者:
[N.Yamamoto, et al., N.Yamamoto, K.Izumi, M.Tanisho, 中山宜典, K.Nishiyama, H.Masui, T.Miyamoto]
通讯作者:
T.Miyamoto
Development of an Electromagnetic Particle Code for Space Propulsion Application Using ECR Discharge
使用 ECR 放电开发用于空间推进应用的电磁粒子代码
DOI:
--
发表时间:
2004
期刊:
24^<th> International Symposium on Space Technology and Science, ISTS 2004-b-11
影响因子:
--
作者:
[N.Yamamoto, et al., N.Yamamoto, K.Izumi, M.Tanisho, 中山宜典, K.Nishiyama, H.Masui, T.Miyamoto, Y.Takao, H.Masui]
通讯作者:
H.Masui
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