RESEARCH AND DEVELOPMENT OF LOW-POWER HALL THRUSTERS WITH CIRCULAR-CROSS-SECTIONAL DISCHARGE CHAMBER, AND ITS INNER PHYSICAL PROCESSES

圆形断面放电室小功率霍尔推进器及其内部物理过程的研制

• 批准号: 16360420
• 负责人: TAHARA Hirokazu
• 金额: $ 9.34万
• 依托单位: OSAKA UNIVERSITY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (B)
• 财政年份: 2004
• 资助国家: 日本
• 起止时间: 2004 至 2006
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-16360420/
• 关键词: HALL THRUSTER; ELECTRIC PROPULSION; SPACE PROPULSION; THRUST PERFORMANCE; PLASMA; LOW POWER; SMALL SATELLITE; 小電力; マイクロサテライト

Effects of magnetic field configuration in Hall thrusters with circular cross-sectional discharge chambers were examined using TCHT-3A and TCHT-3B series Hall thrusters. The results showed that by adjusting the position of peak of radial magnetic flux density the thrust performance was improved. As the position of peak of radial magnetic flux density shifts downstream, the ion loss to the wall and electron current to the anode decrease. However, propellant utilization also decreases because of neutral diffusion. Hence, the optimal position of peak exists.Plume measurements of Hall thruster with circular cross-sectional discharge chamber, named TCHT-2, were carried out. Ion current density measurement showed that the plume divergent angle was not sensitive to propellant mass flow rate and that the propellant utilization decreased as the mass flow rate decreased. Ion energy measurement using RPA indicated that the efficiency of acceleration decreased at low mass flow rate. From the electron temperature and plasma potential distribution inside the discharge chamber obtained by a double probe, the ionization/acceleration region is located at which strong radial magnetic field exists.The miniature Hall thruster TCHT-3A showed that thrust performance declined with scaling down by increase of ion loss. By applying strong radial magnetic field at the downstream region, miniature Hall thruster TCHT-3B achieved higher thrust performance than TCHT-3A did at low power level. It has efficiency (26-39%) in the power range 80-170W.

使用TCHT-3A和TCHT-3B串联霍尔推进器检查了带有圆形横截面放电室的HALL推进器中磁场配置的影响。结果表明，通过调整径向磁通密度的峰位置，提高了推力性能。当径向磁通密度的峰位置下游移动时，离子损失向壁和电子电流降低。但是，由于中性扩散，推进剂的利用率也降低。因此，进行了峰值的最佳位置。进行了带有圆形横截面放电室的大厅推进器（称为TCHT-2）。离子电流密度测量表明，羽流角对推进剂的质量流量不敏感，并且随着质量流速降低，推进剂利用率降低。使用RPA的离子能量测量表明，在低质量流速下，加速度的效率降低。从通过双重探针获得的排放室内的电子温度和血浆电位分布，电离/加速度区域位于其存在强径向磁场的位置。微型霍尔推进器TCHT-3A表明，由于离子损失的增加，推力性能降低而缩小。通过在下游区域应用强径向磁场，微型霍尔推进器TCHT-3B的推力性能比在低功率水平上具有更高的推力性能。它在80-170W的功率范围内具有效率（26-39％）。

项目成果

Effects of Channel Wall Material on Performance and Plasma Characteristics of Hall Thrusters

• 发表时间: 2005
• 作者: H. Tahara;K. Imanaka

Performance Prediction of Hall Thrusters Using One-Dimensional Flowfield Calculation

使用一维流场计算预测霍尔推进器的性能

• 发表时间: 2004
• 期刊: 24^<th> Int.Symp. Space Technology and Science, ISTS 2004-b-53p
• 作者: Hirokazu Tahara;Seiro Yuge;Atsushi Shirasaki;Manuel Martinez-Sanchez
• 通讯作者: Manuel Martinez-Sanchez

Ground-Based Experiment of a Spacecraft Plasma Contactor Using a Hollow Cathode

使用空心阴极的航天器等离子体接触器的地面实验

• 发表时间: 2004
• 期刊: Vacuum 73,3-4
• 作者: Hirokazu Tahara;Seiro Yuge;Atsushi Shirasaki;Manuel Martinez-Sanchez;Hirokazu Tahara et al.;Hirokazu Tahara et al.
• 通讯作者: Hirokazu Tahara et al.

Basic study of electron collection by a bare-tether satellite

• DOI: 10.1016/j.vacuum.2003.12.102
• 发表时间: 2004-04
• 期刊: Vacuum
• 影响因子: 4
• 作者: H. Tahara;Hideki Nishio;T. Onishi

Influence of Magnetic Field Topography and Discharge Channel Structure on Performance of an Anode-Layer Hall Thruster

磁场形貌和放电通道结构对阳极层霍尔推进器性能的影响

• 发表时间: 2006
• 期刊: Proc. 25^<th> Int.Symp. Space Technology and Science, ISTS 2006-b-36
• 作者: Seiro Yuge;Hirokazu Tahara
• 通讯作者: Hirokazu Tahara