中国空间科学技术

中国空间科学技术

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LHT-200E霍尔推力器热特性模拟及热设计研究

包振廷，孙明明*，郭宁，李沛，王尚民，高俊，刘明正   

  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
  • 收稿日期:2025-07-29 修回日期:2025-09-21 录用日期:2025-10-09 发布日期:2026-04-09

Study on thermal characteristics and thermal design of LHT-200E Hall thruster

BAO Zhenting, SUN Mingming*, GUO Ning, LI Pei, WANG Shangmin, GAO Jun, LIU Mingzheng   

  1. Science and Technology on Vacuum Technology and Physics Laboratory, Lanzhou Institute of Physics, Lanzhou 730000, China
  • Received:2025-07-29 Revision received:2025-09-21 Accepted:2025-10-09 Online:2026-04-09

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摘要： 温度分布对大功率霍尔推力器的工作稳定性与可靠性具有显著影响。为获得LHT-200E霍尔推力器在额定功率工况下的热耗及温度分布情况，采用有限元分析对推力器分别进行了12.5kW工况下的热模型验证及校准，以及15kW额定工况下的热特性分析及热设计。通过仿真获得LHT-200E霍尔推力器在改变放电室支架材料、添加不同位置的散热片或散热板、导磁底座分体3种热设计方式下的温度场分布情况，验证热设计的有效性。结果显示：当推力器工作在12.5kW工况下，总热耗为2510W，即占总功率20.1%时，温度模拟结果与实测值最为接近。最大误差出现在推力器内线圈且达到了6.2%，主要是由于接触热阻设置不准确，但误差在热模型建立允许范围内。同时经仿真比对，针对15kW额定工况，在合理运用3种热设计的情况下，导磁底座的温度最大可降低约50℃，内线圈的温度可降低约40℃。3种热设计方式中，添加散热板是最显著的降温设计，而改变放电室支架材料与导磁底座分体的效果则不显著。通过对比3种热设计方式结果，采用高导热率放电室支架材料结合散热板设计，可有效降低推力器关键部件温度，改善其温度分布情况，提高任务可靠性。

关键词: 霍尔推力器, 热特性, 有限元分析, 热分析, 热设计

Abstract: The temperature distribution significantly influences the operational stability and reliability of the high-power Hall thruster(HPHET). To investigate the thermal dissipation and temperature distribution of LHT-200E Hall thruster under rated power conditions, finite element analysis (FEA) is employed. The thermal model of the thruster is first validated and calibrated under a 12.5kW operating condition. Subsequently, thermal characteristic analysis and thermal design optimization are conducted for the 15kW rated condition. Through simulations, the temperature field distribution under three thermal design approaches, i.e., changing the material of the discharge chamber support, adding heat sinks or heat plates at different positions, and segmenting the magnetic base, is analyzed to verify the effectiveness of the thermal designs. The results show that, under the 12.5kW condition, the total heat dissipation is 2510W, accounting for 20.1% of the total power, and the simulated temperature results are the closest to the measured values with a maximum error of 6.2% occurring in the inner coil, primarily attributing to inaccuracies in contact thermal resistance settings, which are within the permissible range of thermal model establishment. Comparative simulations for the 15kW condition demonstrate that, when the three thermal design approaches are appropriately applied, the temperature of the magnetic base can be reduced by approximately 50℃, and the temperature of the inner coil can be reduced by approximately 40℃.Among the three thermal design methods, adding heat plates is the most effective cooling approach, whereas changing the discharge-chamber support material and segmenting the magnetic base produce only moderate improvements. Comparing the three methods shows that combining a high-thermal-conductivity bracket for the discharge chamber with a heat-plate design effectively lowers the temperatures of critical thruster components, evens out their temperature distribution and enhances mission reliability.

Key words: Hall thruster, thermal characteristics, finite element analysis, thermal analysis, thermal design

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