60 mm口径霍尔推力器放电特性数值模拟与试验

Numerical Simulation and Experiment on the Discharge Characteristics of a 60 mm Diameter Hall Thruster

为了明晰小功率霍尔推力器放电特性,为后续工程应用及优化提供帮助,基于兰州空间技术物理研究所研制的60 mm口径小功率霍尔推力器LHT-60,建立了二维轴对称模型,利用流体方法对推力器放电室内等离子体放电特性进行了数值模拟,获得了推力器启动过程中的等离子体分布变化,并模拟推力器额定工况稳态下的等离子体、电子温度以及空间电势等关键参数。额定工况下计算推力和阳极比冲分别为21.18 mN、1257 s。同时,为验证推力器宽功率范围工作能力,在阳极流率1.1~1.7 mg/s,阳极电压280~350 V条件下开展了试验,并与数值模拟结果对比分析,结果表明误差在10%左右。

In order to explore the discharge characteristics of low-power Hall thrusters and provide guideline for future optimization and engineering applications,a two-dimensional axisymmetric model was established,based on a 60 mm diameter low power Hall thruster named LHT-60,designed by Lanzhou Institute of Physics.The plasma characteristics in its discharge channel were simulated in fluid method.The variation of the plasma density along the channel in the process of igniting was obtained,and the electron temperature and the spatial potential were also simulated.The calculated thrust and special impulse under rated condition was 21.18 mN and 1257 s,respectively.The experiment were carried out with thrust stand under the conditions of of anode flow rate 1.1~1.7 mg/s and anode voltage 280~350 V to verify the ability of LHT-60 operating at various conditions.The numerical results coincide with the experiment as well.The results show that the maximum error is no more than 10%.