Abstract: :In order to optimize thermal design of a LHT-100 Hall thruster，the thermal behaviour of a LHT-100 Hall thruster was described. Warm-up time，steady-state temperature distribution and space environment simulation for the thruster were simulated by the finite element analysis software. The simulation results were compared with thermal-balance experiment results，which show the high temperature components are discharge chamber，anode and magnetizer，and the thermal weakness components include inner circuitry and anode insulation parts，whose temperature are up to 401～421℃ and 141～381℃. Thermal design optimization measures suggest that increasing heat shield between discharge chamber and inner circuitry will reduce the inner circuitry temperature about 80～90℃，and thermal deformation occurred in the anode insulation parts is the core factor which influences the reliability of the Hall thruster，which should be considered in thermal design.

Key words: Hall thruster；Thermal analysis；Thermal design；Temperature distribution

摘要： 为了对LHT-100霍尔推力器提出热设计优化措施，采用有限元仿真软件进行LHT-100霍尔推力器的稳态、瞬态及空间在轨环境模拟热分析研究，并通过热平衡试验进行了结果比对。分析及试验结果表明，处于工作状态时霍尔推力器的高温部件主要是放电腔、阳极和导磁底座，而受高温影响薄弱部件内线圈、气路组件的温度则分别达到了约401～421℃和141～381℃。热设计优化建议为，在放电腔与内线圈之间增加独立热屏结构后可以有效降低内线圈温度约80～90℃，在阳极气路组件上存在的热应力会是影响霍尔推力器可靠性的重要因素，需要在热设计中得到充分考虑。

关键词: 霍尔推力器；热分析；热设计；温度分布