IMPROVEMENT OF HALL THRUSTER PERFORMANCE

霍尔推进器性能的改进

• 批准号: 03452096
• 负责人: ARAKAWA Yoshihiro
• 金额: $ 3.97万
• 依托单位: UNIVERSITY OF TOKYO
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for General Scientific Research (B)
• 财政年份: 1991
• 资助国家: 日本
• 起止时间: 1991 至 1993
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-03452096/
• 关键词: THRUSTER; PERFORMANCE; PLASMA; ELECTRIC PROPULSION; HALL CURRENT; HOLLOW CATHODE; ROCKET; ホールスラスタ; 推進性能; ホ-ルスラスタ; 電磁加速

A magnetic circuit that largely influences Hall thruster performance was designed by using two-dimensional FEM magnetic analysis code which was developed previously. A solenoidal coil was positioned at the center of acceleration channel in order to have high radial magnetic fields applied on it.Based on the above circuit design, the acceleration channel of a thruster was designed and fabricated. In addition, power supplies for plasma production, ion acceleration, and neutralization were ordered and assembled.The thruster was operated in the vacuum system which consists of a 0.8 m diam. and 2.5 m long chamber and 10,000 1/s pumping system. We obtained stable arc discharge as well as normal plasma production and ion beam extraction. Also, discharge voltage-current characteristics were examined and show a general tendency for this kind of thruster.Increasing an input power up to 1.5kW, thrust measurement was done to estimate thruster performance. Ion beam current was also measured to obtain acceleration efficiency and to investigate the effect of channel geometry, field strength, and operating conditions on it.A hollow cathode was installed on the thruster in place of a filament cathode. With the hollow cathode, a maximum thrust efficiency of 34 % was obtained when xenon gas was used as the propellant.

利用自行开发的二维有限元磁场分析程序，设计了对霍尔推力器性能有较大影响的磁路。在加速通道中心设置螺线管线圈，使其具有较强的径向磁场，并在此基础上设计制作了推力器加速通道。此外，还订购和组装了用于产生等离子体、离子加速和中和的电源。推进器在直径为0.8米的真空系统中运行。2.5m长的水室和万分之一的S抽水系统。我们获得了稳定的弧光放电以及正常的等离子体产生和离子束引出。此外，还研究了这种推进器的放电伏安特性，得出了这种推进器的总体趋势。将输入功率增加到1.5kW时，进行了推力测量，以评估推进器的性能。为了获得加速效率，还测量了离子束电流，并研究了通道几何形状、场强和操作条件对加速效率的影响。采用空心阴极，以氙气为推进剂时，推力效率最高可达34%。

项目成果

Kimiya Komurasaki: "Two-Dimensional Numerical Model of Plasma Flow in a Hall Thruster" 23rdIEPC. 93-230 (1993)

Kimiya Komurasaki：“霍尔推进器中等离子体流的二维数值模型”第 23 届IEPC。

Kimiya Komurasaki: "Hall Current Ion-Thruster Performance" Journal of Propulsion and power. 8-1. 1212-1216 (1992)

Kimiya Komurasaki：“霍尔电流离子推进器性能”推进与动力杂志。

小紫公也: "ホールスラスタの性能とプラズマ加速過程" 日本航空宇宙学会誌. 40. 568-575 (1992)

Kimiya Komurasaki：“霍尔推进器的性能和等离子体加速过程”，日本航空学会杂志 40. 568-575 (1992)。

Kimiya Komurasaki: "Two-Dimensional Numerical Model of Plasma Flow in a Hall Thruster" 23rd IEPC. 93-230 (1993)

Kimiya Komurasaki：“霍尔推进器中等离子体流的二维数值模型”第 23 届 IEPC。

Kimiya Komurasaki: "Hall Thruster Performance and Plasma Acceleration Processes" Journal of Japan Society for Aeronautical and Space Sciences. 40. 568-575 (1992)

Kimiya Komurasaki：“霍尔推进器性能和等离子体加速过程”日本航空航天学会杂志。