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Collisionless electron cooling in a plasma thruster plume: experimental validation of a kinetic model

机译：等离子体推进器羽流中的碰撞电子冷却：动力学模型的实验验证

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摘要

A central challenge in the modeling of the near-collisionless expansion of a plasma thruster plume into vacuum is the inadequacy of traditional fluid closure relations for the electron species, such as isothermal or adiabatic laws, because the electron response in the plume is essentially kinetic and global. This work presents the validation of the kinetic plasma plume model presented in (Merino et al 2018 Plasma Sources Sci. Technol. 27 035013) against the experimental plume measurements of a SPT-100-ML Hall thruster running on xenon presented in (Giono et al 2018 Plasma Sources Sci. Technol. 27 015006). The model predictions are compared against the experimentally-determined axial profiles of electric potential, electron density, and electron temperature, and the radial electric potential profile, for 6 different test cases, in the far expansion region between 0.5 and 1.5m away from the thruster exit. The model shows good agreement with the experimental data and the error is within the experimental uncertainty. The extrapolation of the model to the thruster exit plane and far downstream is consistent with the expected trends with varying discharge voltage and mass flow rate. The lumped-model value of the polytropic cooling exponent γ is similar for all test cases and varies in the range 1.26–1.31.
机译：等离子体推力器羽流向真空的近无碰撞膨胀建模中的一个核心挑战是电子物种的传统流体闭合关系（如等温或绝热定律）的不足，因为羽流中的电子响应本质上是动力学和全局的。这项工作验证了（Merino等人2018《等离子体源科学技术》27 035013）中提出的动力学等离子体羽流模型与（Giono等人2018《等离子体源科学技术》27 015006）中提出的运行在氙气上的SPT-100-ML霍尔推力器的实验羽流测量结果。在距离推进器出口0.5至1.5m的远膨胀区域，将模型预测与实验确定的电势、电子密度和电子温度的轴向分布以及6种不同试验情况下的径向电势分布进行比较。该模型与实验数据吻合良好，误差在实验不确定度范围内。模型外推到推力器出口平面和远下游，与放电电压和质量流量变化的预期趋势一致。所有试验情况下，多方冷却指数γ的集总模型值相似，变化范围为1.26–1.31。

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