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首页> 外文会议>International conference on computational and experimental methods in multiphase and complex flow >Computational multi-component modelling of electron transport and ohmic heating inside a micro arc-jet thruster
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Computational multi-component modelling of electron transport and ohmic heating inside a micro arc-jet thruster

机译：微型电弧喷射推进器内部电子传输和欧姆加热的计算多部件建模

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Fuel mass is one of the main economical and technical restrictions while designing space propulsion systems. Given the high costs related to the transport of mass into space, the necessary fuel mass for accomplishment of the mission should be minimised. For an optimum "thrust/fuel consumption ratio" the gas exit velocity must be maximised. In this research this is achieved through the heating of the micro gas flow by an electrical arc inside the sub-sonic region of the propulsion system. The electrical arc induces a partial ionisation of the propellant gas. Because of the very low mass flow, the gap of the plasma channel has a width of just a few hundred microns. The electrical arc consists of electrons being accelerated through this small gap by the charged walls of the microchannel. The electrons move in a cross flow compared to the propellant gas. The computational results are validated with the experimental data. Through this investigation a very efficient form of electrodynamic heating-modelling is developed. The very good results show the quality of the present method and encourage further utilisation and development. For this reason this model will be used for the optimisation and the computational engineering pre-development of future thermo-electric propulsion systems.
机译：在设计空间推进系统时，燃料质量是主要的经济和技术限制之一。鉴于与将质量运输到太空有关的高额费用，应尽量减少完成任务所需的燃料量。为了获得最佳的“推力/燃料消耗比”，必须使气体出口速度最大化。在这项研究中，这是通过推进系统的亚音速区域内的电弧加热微气流来实现的。电弧引起推进剂气体的部分电离。由于质量流量非常低，等离子通道的间隙只有几百微米的宽度。电弧由电子组成，该电子通过微通道的带电壁通过这个小间隙加速。与推进剂气体相比，电子以横流运动。计算结果得到了实验数据的验证。通过这项研究，开发了一种非常有效的电动加热建模形式。很好的结果表明了本方法的质量，并鼓励了进一步的利用和发展。因此，该模型将用于未来热电推进系统的优化和计算工程的预开发。

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