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

基本信息

  • 批准号:
    16360420
  • 负责人:
  • 金额:
    $ 9.34万
  • 依托单位:
  • 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

项目摘要

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.
用TCHT-3A和TCHT-3B系列霍尔推进器研究了圆形截面放电室霍尔推进器中磁场结构的影响。结果表明,通过调整径向磁通密度峰值的位置,改善了推力性能。随着径向磁通密度峰值位置向下游移动,流向壁面的离子损失和流向阳极的电子电流减小。然而,由于中性扩散,推进剂利用率也会下降。对TCHT-2圆形截面放电室霍尔推力器进行了羽流测量。离子流密度测量表明,羽流发散角对推进剂质量流量不敏感,推进剂利用率随质量流量的减小而降低。用RPA测量离子能量表明,在低质量流量下,加速效率降低。从双探头测得的放电室内电子温度和等离子体电势分布可知,电离/加速区域位于径向磁场较强的区域。小型霍尔推进器TCHT-3A显示,随着离子损耗的增加,推力性能随尺度减小而下降。小型霍尔推力器TCHT-3B通过在下游施加强的径向磁场,在低功率下获得了比TCHT-3A更高的推力性能。它的效率在80-170W范围内(26%-39%)。

项目成果

期刊论文数量(9)
专著数量(0)
科研奖励数量(0)
会议论文数量(0)
专利数量(0)
Effects of Channel Wall Material on Performance and Plasma Characteristics of Hall Thrusters
  • DOI:
  • 发表时间:
    2005
  • 期刊:
  • 影响因子:
    0
  • 作者:
    H. Tahara;K. Imanaka
  • 通讯作者:
    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
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
  • DOI:
  • 发表时间:
    2004
  • 期刊:
  • 影响因子:
    0
  • 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.
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
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:
  • 影响因子:
    4
  • 作者:
    H. Tahara;Hideki Nishio;T. Onishi
  • 通讯作者:
    H. Tahara;Hideki Nishio;T. Onishi
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TAHARA Hirokazu其他文献

TAHARA Hirokazu的其他文献

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{{ truncateString('TAHARA Hirokazu', 18)}}的其他基金

Development of High-Performance, Long-Lifetime and High-Power Magneto-Plasma-Dynamic Thrusters for In-Space Exploration
开发用于太空探索的高性能、长寿命和高功率磁等离子体动力推进器
  • 批准号:
    17H03484
  • 财政年份:
    2017
  • 资助金额:
    $ 9.34万
  • 项目类别:
    Grant-in-Aid for Scientific Research (B)
Research on Low-Temperature Material Processings Using Supersonic Plasma Jets
超音速等离子射流低温材料加工研究
  • 批准号:
    23656543
  • 财政年份:
    2011
  • 资助金额:
    $ 9.34万
  • 项目类别:
    Grant-in-Aid for Challenging Exploratory Research
RESEARCH AND DEVELOPMENT OF HIGH-SPECIFIC-IMPULSE AND LONG-LIFETIME HALL THRUSTERS
高比冲长寿命霍尔推进器的研发
  • 批准号:
    22360360
  • 财政年份:
    2010
  • 资助金额:
    $ 9.34万
  • 项目类别:
    Grant-in-Aid for Scientific Research (B)
RESEARCH ON ENHANCEMENT OF IMPULSE FOR ELECTROTHERMAL PULSED PLASMA THRUSTERS ONBOARD SMALL SATELLITES
小卫星电热脉冲等离子体推进器脉冲增强研究
  • 批准号:
    19360382
  • 财政年份:
    2007
  • 资助金额:
    $ 9.34万
  • 项目类别:
    Grant-in-Aid for Scientific Research (B)
Plasma Flow Structure of Direct-Current Arcjet Thrusters and Its Spacecraft Interaction Research
直流电弧喷射推进器等离子流结构及其与航天器相互作用研究
  • 批准号:
    13450398
  • 财政年份:
    2001
  • 资助金额:
    $ 9.34万
  • 项目类别:
    Grant-in-Aid for Scientific Research (B)
Research and Development of Ground Simulation Methods for Spacecraft Environment, and Degradation Experiments of Spacecraft Materials
航天器环境地面模拟方法研究与进展及航天器材料降解实验
  • 批准号:
    09555301
  • 财政年份:
    1997
  • 资助金额:
    $ 9.34万
  • 项目类别:
    Grant-in-Aid for Scientific Research (B)
Flowfield Structure and Acceleration Process in Quasi-Steady Magneto-Plasma-Dynamic (MPD) Arc Channels
准稳态磁等离子体动力 (MPD) 电弧通道中的流场结构和加速过程
  • 批准号:
    07651123
  • 财政年份:
    1995
  • 资助金额:
    $ 9.34万
  • 项目类别:
    Grant-in-Aid for Scientific Research (C)

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