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首页> 外文期刊>Plasma Sources Science & Technology >A fluid formalism for low-temperature plasma flows dedicated to space propulsion in an unstructured high performance computing solver
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A fluid formalism for low-temperature plasma flows dedicated to space propulsion in an unstructured high performance computing solver

机译：用于在非结构化高性能计算求解器中专用于空间推进的低温等离子体流体的流体形式主义

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With the increased interest in electric propulsion for space applications, a wide variety of electric thrusters have emerged. For many years, Hall effect thrusters have been the selected technology to sustain observation and telecommunication satellites thanks to their advantageous service lifetime, their high specific impulse and high power to thrust ratio. Despite several studies on the topic, the Hall thruster electric discharge remains still poorly understood. With the increase of available computing resources, numerical simulation becomes an interesting tool in order to explain some complex plasma phenomena. In this paper, a fluid model for plasma flows is presented for the numerical simulation of space thrusters. Fluid solvers often exhibit strong hypotheses on electron dynamics via the drift-diffusion approximation. Some of them use a quasi-neutral assumption for the electric field which is not adapted near walls due to the presence of sheaths. In the present model, all these simplifications are removed and the full set of plasma equations is considered for the simulation of low-temperature plasma flows inside a Hall thruster chamber. This model is implemented in the unstructured industrial solver AVIP, efficient on large clusters and adapted to complex geometries. Electrical sheaths are taken into account as well as magnetic field and majors collision processes. A particular attention is paid on a precise expression of the different source terms for elastic an inelastic processes. The whole system of equations with adapted boundary conditions is challenged with a simulation of a realistic 2D r–z Hall thruster configuration. The full-fluid simulation exhibits a correct behavior of plasma characteristics inside a Hall effect thruster. Comparisons with results from the literature exhibit a good ability of AVIP to model the plasma inside the ionization chamber. Finally a specific attention was brought to the analysis of the thruster performances.
机译：随着人们对空间应用电力推进的兴趣不断增加，出现了各种各样的电力推进器。多年来，霍尔效应推力器由于其优越的使用寿命、高比冲和高功率推力比，一直是维持观测和通信卫星的首选技术。尽管对这一主题进行了几项研究，霍尔推力器的放电仍然知之甚少。随着可用计算资源的增加，为了解释一些复杂的等离子体现象，数值模拟成为一种有趣的工具。本文提出了一种用于空间推进器数值模拟的等离子体流动流体模型。流体解算器通常通过漂移-扩散近似对电子动力学表现出强大的假设。其中一些使用了电场的准中性假设，但由于存在护套，该假设不适用于墙壁附近。在本模型中，取消了所有这些简化，并考虑了用于模拟霍尔推力器室内低温等离子体流动的全套等离子体方程。该模型在非结构化工业求解器AVIP中实现，在大型集群中效率高，适用于复杂几何体。考虑了电护套以及磁场和碰撞过程。特别注意弹性和非弹性过程的不同源项的精确表达式。通过模拟真实的2D r–z霍尔推力器配置，挑战了具有自适应边界条件的整个方程组。全流体模拟展示了霍尔效应推力器内等离子体特性的正确行为。与文献结果的比较表明，AVIP能够很好地模拟电离室内的等离子体。最后，对推力器的性能进行了分析。

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