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首页> 外文期刊>Journal of applied mathematics >Numerical Study of Hall Thruster Plume and Sputtering Erosion
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Numerical Study of Hall Thruster Plume and Sputtering Erosion

机译：霍尔推力器羽流和溅射侵蚀的数值研究

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Potential sputtering erosion caused by the interactions between spacecraft and plasma plume of Hall thrusters is a concern for electric propulsion. In this study, calculation model of Hall thruster’s plume and sputtering erosion is presented. The model is based on three dimensional hybrid particle-in-cell and direct simulation Monte Carlo method (PIC/DSMC method) which is integrated with plume-wall sputtering yield model. For low-energy heavy-ion sputtering in Hall thruster plume, the Matsunami formula for the normal incidence sputtering yield and the Yamamura angular dependence of sputtering yield are used. The validation of the simulation model is realized through comparing plume results with the measured data. Then, SPT-70’s sputtering erosion on satellite surfaces is assessed and effect of mass flow rate on sputtering erosion is analyzed.
机译：由航天器和霍尔推进器的等离子羽流之间的相互作用引起的潜在溅射腐蚀是电推进的一个问题。在这项研究中，提出了霍尔推进器羽流和溅射腐蚀的计算模型。该模型基于三维混合单元内颗粒和直接模拟蒙特卡洛方法（PIC / DSMC方法），并与羽壁溅射产率模型集成在一起。对于霍尔推进器羽流中的低能重离子溅射，使用法线入射溅射量的Matsunami公式和溅射产量的Yamamura角依赖性。通过将羽流结果与测量数据进行比较，可以实现对仿真模型的验证。然后，评估SPT-70在卫星表面的溅射腐蚀，并分析质量流量对溅射腐蚀的影响。

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