HET-450大功率霍尔电推力器仿真分析及试验

Simulation analysis and test verification of HET-450 High-power Hall electric thruster

针对大功率霍尔推力器耐受强热载荷不易稳定工作、宽放电电压范围调整难以高效电磁调控等关键难点,兰州空间技术物理研究所与哈尔滨工业大学联合开展了10 kW级以上大功率霍尔推力器技术研究,开展了热分析设计,并建立热仿真模型,计算获得关键组件稳态温度,结果显示各部位温度均满足设计要求;同步建立了PIC仿真模型,进行了80 mg/s固定流率下,不同电压下电离特性分析,结果表明推力器放电腔口径较大情况下,电压低会使工质利用率降低从而导致推力器效率低;进一步,开展性能分析,得出600 V阳极效率低于500 V时工况,分析为电离不充分和壁面能量损失所致;此外,基于实验样机开展了试验研究,实现30 kW功率下的稳定工作,表明针对性热防护设计具有较好效果,并采用激光干涉推力测量法,获得推力为1.33 N,与仿真数据所得1.38 N偏差在5%以内,具有较高的符合度,表明推力器设计合理有效。

Compared to other high power electric propulsion,Hall thruster has significant advantages in Thruster power ratio and Specific impulse.However,the increase in power brings many complex physical problems.Therefore,aiming at the key difficulties of high-power Hall thruster,such as the difficulty of working stably under strong thermal load and the difficulty ofadjusting the wide discharge voltage range and efficient electromagnetic regulation,Lanzhou Institute of Physics(LIP)and Harbin Institute of Technology(HIT)had jointly launched the over-10 kW high power Hall thruster.The thermal analysis and design were carried out,and the thermal simulation model was established to calculate the steady-state temperature of the key components.The results showed that the temperature of each part met the design requirements.The PIC simulation model was established synchronously,and the ionization characteristics were analyzed under different voltages at fixed flow rate of 80 mg/s.The results showed that low current would reduce the utilization rate of working medium and lead to low efficiency of thruster under the condition of large discharge cavity diameter.Further,the performance analysis was carried out to obtain the working condition of 600 V anode efficiency lower than 500 V,which was caused by insufficient ionization and wall energy loss.In addition,based on the experimental prototype,experimental research under 30 kw power was carried out and the result suggests that corresponding design has a good effect.The thermal and l aser interference measurement method was adopted to obtain the thrust of 1.33 N,which deviates from the simulation data 1.38 N by an error within 5%.Therefore,the thruster design in this paper was reasonable and effective.