Effect of a magnetic field in simulating the plume field of an anode layer Hall thruster
Effect of a magnetic field in simulating the plume field of an anode layer Hall thruster
复制标题
DOI：
10.1063/1.3055399
复制
发表时间：
2009-01
影响因子：
3.2
通讯作者：
Y. Choi;I. Boyd;M. Keidar
中科院分区：
文献类型：
--
作者：
Y. Choi;I. Boyd;M. Keidar
在这项研究中，我们对D55阳极层霍尔推进器的氙气等离子体羽流流场进行了轴对称模拟。数值模拟采用了粒子-流体混合方法。霍尔推进器出口周围的磁场也包括在计算中。由流体动力学模型得到的等离子体性质被用作模拟的边界条件。电子性质用Boltzmann模型和详细流体模型计算，重粒子碰撞用直接模拟蒙特卡罗方法模拟，离子在电场中的输运用粒子格子方法模拟。通过与各种测量数据的比较，对模拟的准确性进行了评估。结果表明，磁场对详细模型中等离子体的分布有显著影响。在零磁场的情况下，等离子体在距推力器出口10 mm处的电势为80V，当有磁场存在时，电势降至60V。预测的结果是……
In this study, we present axisymmetric simulations of xenon plasma plume flow fields from a D55 anode layer Hall thruster. A hybrid particle-fluid method is used for the simulations. The magnetic field surrounding the Hall thruster exit is included in the calculation. The plasma properties obtained from a hydrodynamic model are used as boundary conditions for the simulations. The electron properties are calculated using the Boltzmann model and a detailed fluid model, collisions of heavy particle are modeled with the direct simulation Monte Carlo method, and ion transport in the electric field uses the particle-in-cell technique. The accuracy of the simulation is assessed through comparison with various measured data. It is found that a magnetic field significantly affects the profile of the plasma in the detailed model. The plasma has a potential of 80 V at 10 mm from the thruster exit in the case of zero magnetic field, which decreases to 60 V when the magnetic field is included. Results predicted by the...