地面真空试验设施中霍尔推力器羽流的电流路径模型:测量和观察。

Journal of electric propulsion Pub Date : 2024-01-01 Epub Date: 2024-12-30 DOI:10.1007/s44205-024-00097-8
David R Jovel, Janice D Cabrera, Mitchell L R Walker
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引用次数: 0

摘要

之前的一篇论文介绍了一个电流路径模型,该模型代表了霍尔效应推进器(HET)和地面真空测试设施运行环境之间的电耦合。在这项工作中,我们在氪上运行了一个4.5 kW, 15 a和6 kW, 20 a的7 kW级HET,以量化电流路径模型的各个方面,以表征金属真空室在推进器放电电路中作为放电电流的函数所起的作用。在HET操作期间,使用直径5.08 cm的不锈钢平面电极阵列测量了47个设施附近壁面位置的远场离子和电子饱和电流。此外,使用Langmuir探针获得了设施内距离设施壁25 cm的三个不同位置的等离子体特性。实验结果表明,推力器束离子不容易与阴极电子中和,而是与金属腔壁提供的自由电子中和。此外,在背景等离子体环境下测量到显著的电荷交换(CEX)离子电流,约占平面电极阵列测量到的总离子电流的23%。因此,金属真空室表面有利于两种离子群的电荷中和。此外,设施墙壁附近的等离子体环境不均匀,估计等离子体护套电容在0.45µF到1.79µF之间。进一步的分析表明,设施壁上的等离子体护套表现得像一个平行的RC电路,潜在地隐藏了推进器的交流特性。固有的等离子体振荡引起电感效应,其电感在76.5 nH和101.4 nH之间变化。因此,真空试验装置运行环境所引入的电容效应和电感效应会影响高压放电的动态特性。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Current pathways model for hall thruster plumes in ground-based vacuum test facilities: measurements and observations.

A previous companion paper introduced a current pathways model that represents the electrical coupling between the Hall effect thruster (HET) and the ground-based vacuum test facility operational environment. In this work, we operated a 7-kW class HET at 4.5 kW, 15 A and 6 kW, 20 A on krypton to quantify aspects of the current pathways model to characterize the role metal vacuum chambers play in the thruster's discharge circuit as a function of discharge current. During HET operation, far-field ion and electron saturation currents at 47 near-facility wall locations were measured using an array of 5.08 cm diameter, stainless-steel planar electrodes. In addition, the plasma properties at three distinct locations within the facility, 25 cm from the facility wall, were obtained using Langmuir probes. Experimental results show that thruster beam ions do not readily neutralize with cathode electrons and instead neutralize with the free electrons provided by the metallic chamber wall. In addition, significant charge-exchange (CEX) ion current was measured in the background plasma environment and constituted about 23% of the total ion current measured by the planar electrode array. Thus, the metallic vacuum chamber surfaces facilitate charge neutralization for both ion populations. Additionally, the plasma environment near the facility walls was characterized to be non-uniform with an estimated plasma sheath capacitance ranging between 0.45 µF and 1.79 µF. Further analysis shows that the plasma sheath at the facility wall behaves like a parallel RC circuit, potentially concealing the thruster's AC characteristics. Inherent plasma oscillations give rise to inductive effects with inductances that varied between 76.5 nH and 101.4 nH. Hence, the dynamic characteristics of the HET's discharge are influenced by the capacitive and inductive effects introduced by the vacuum test facility operational environment.

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