北京航空航天大学学报 ›› 2020, Vol. 46 ›› Issue (8): 1476-1484.doi: 10.13700/j.bh.1001-5965.2019.0484

• 论文 • 上一篇    下一篇

基于CFD的10 cm氙离子推力器阳极推进剂供给方式优化

胡竟1,2, 杨福全1, 郭德洲1, 高俊1, 郑茂繁1   

  1. 1. 兰州空间技术物理研究所 真空技术与物理重点实验室, 兰州 730000;
    2. 北京航空航天大学 材料科学与工程学院, 北京 100083
  • 收稿日期:2019-09-05 发布日期:2020-08-27
  • 通讯作者: 胡竟 E-mail:hjing37615486@163.com
  • 作者简介:胡竟 男,博士研究生,工程师。主要研究方向:放电等离子电推力器技术与磁性材料应用。
  • 基金资助:
    民用航天预先研究项目(D010509);国家自然科学基金(61601210)

Optimization of anode propellant allocation manner of 10 cm xenon ion thruster based on CFD

HU Jing1,2, YANG Fuquan1, GUO Dezhou1, GAO Jun1, ZHENG Maofan1   

  1. 1. Science and Technology on Vacuum Technology and Physics Laboratory, Lanzhou Institute of Physics, Lanzhou 730000, China;
    2. School of Materials Science and Engineering, Beihang University, Beijing 100083, China
  • Received:2019-09-05 Published:2020-08-27
  • Supported by:
    Civil Space Advance Research Project (D010509); National Natural Science Foundation of China (61601210)

摘要: 离子推力器阳极推进剂在放电室内的浓度分布及其变化梯度的设计是放电室放电模式可靠性设计的关键技术之一,直接影响到放电室内推进剂的电离效率及放电稳定性。针对航天器在轨多目标飞行任务对10 cm氙离子推力器的应用需求,为提高10 cm氙离子推力器放电室空腔内阳极推进剂供给的均匀性,实现推进剂利用率的有效提升,运用计算流体动力学(CFD)理论,建立了包括阳极推进剂、进气管和分配环在内的CFD阳极环模型,研究了未发生气体放电情况下,不同供给方式时阳极环内阳极推进剂的压强与流速变化情况。在此基础上,分析了阳极推进剂供给方式对10 cm氙离子推力器放电室空腔内阳极推进剂分布特性的影响作用关系。将优化前后的阳极环在10 cm氙离子推力器中进行了性能对比,结果表明:优化后阳极推进剂电离损耗由277.9 W/A降至241.2 W/A,放电室阳极推进剂利用率由91.7%提升至98.4%,验证了CFD计算结果的正确性与方法的可行性。研究结果为离子推力器放电室拓扑结构设计与优化提供了方法。

关键词: 计算流体力学(CFD), 10 cm氙离子推力器, 阳极推进剂, 供给方式, 电离损耗, 推进剂利用率

Abstract: The concentration distribution of anode propellant in discharge chamber and its gradient design is one of the most important techniques in discharging mode reliability design, and it directly influences the ionization efficiency and discharge stability of anode propellant. Aimed at the application requirement of multi-objective attitude and orbit control of spacecraft for 10 cm xenon ion thruster, by using the Computational Fluid Dynamics (CFD) method, the CFD model for analyzing the propellant allocation manner is established, which consists of the propellant, the inner tube and the distribution ring. The pressure and velocity distribution rules of anode-ring propellant in different allocation manners were studied without discharge progress to ameliorate circumferential uniformity of propellant in 10 cm xenon ion thruster discharge chamber and improve its utilization efficiency. On this basis, the influences of anode propellant allocation manner on the propellant distribution characteristics in discharge chamber were analyzed. And the performance of anode-ring before and after optimization in 10 cm xenon ion thruster are compared. The results show that after the improvement of the anode propellant allocation manner, the ion production cost drops from 277.9 W/A to 241.2 W/A, and the propellant utilization efficiency in discharge chamber increases from 91.7% to 98.4%, which verify the correctness of CFD calculation results and the feasibility of the CFD method. The results of this research will certainly provide method for the topological structure design and optimization of the discharge chamber of ion thruster.

Key words: Computational Fluid Dynamics (CFD), 10 cm xenon ion thruster, anode propellant, allocation manner, ion production cost, propellant utilization efficiency

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