霍尔推力器热模型研究

为了对霍尔推力器的热分析研究提供准确的能耗加载条件,开展了霍尔推力器稳态工况下的热模型研究。基于等离子体理论,分析放电室内各项能量损耗机理,并建立各能量损耗与推力器工作参数、性能参数和结构参数的相关函数,系统地得到了霍尔推力器的完整热模型。以LHT100推力器为研究对象,热模型计算结果显示:额定工况下束流能量损耗约889 W,壁面能量损耗约300 W,阳极能量损耗约44 W,电离能量损耗约43 W,辐射能量损耗约34 W等。以此能量损耗作为热边界条件进行有限元分析,并开展热平衡试验进行验证,计算结果与试验结果吻合较好,最大误差小于5%。

Thermal model of Hall thruster

To provide energy loss loading conditions for the thermal analysis of Hall thruster, a thermal model of Hall thruster is developed. Based on the plasma theory, the mechanism of various energy losses in discharge chamber is analyzed, and related functions are established between these energy losses and operation, performance parameters and structural parameters. At last the complete thermal model of Hall thruster is obtained. The thermal model for LHT100 thruster is calculated. The following results under the steady operation are obtained: the beam energy loss is about 889 W, the energy loss at wall is about 300 W, the anode energy loss is about 44 W, the ionization energy loss is 43 W, and the radiation energy loss is 34 W, respectively. Taking these energy losses as loading conditions to perform finite element thermal analysis and using thermal balance to validate experimentally, the results indicate that the calculated values agree well with the experimental ones, the maximum error is no more than 5%.