Characterization of the Plasma in a Hall Thruster
Characterization of the Plasma in a Hall Thruster
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霍尔推进器中等离子体的表征
DOI：
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发表时间：
2001
期刊：
影响因子：
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通讯作者：
E. Ahedo
中科院分区：
文献类型：
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作者：
E. Ahedo
安切斯省麻省理工学院航空航天学院，剑桥，马萨诸塞州 02139 IEPC-01-017 提出了霍尔推进器中等离子体轴向放电的模型，其中包括介电壁损耗和热传导的影响。等离子体与电介质壁的相互作用通过三个频率来体现，这三个频率考虑了离子复合、能量损失和近壁电导率。这些频率取决于介电壁的二次发射和径向等离子体流的动力学。能量损失集中在加速区，降低了等离子体温度，近壁电导率微乎其微，离子复合在扩散区很高。热传导的主要影响是电离区域周围温度分布的平滑，以及对找到有效固定解的参数范围的强烈限制。
anchez Dep. of Aeronautics & Astronautics, M.I.T., Cambridge, MA 02139 IEPC-01-017 A model of the plasma axial discharge in a Hall thruster, which includes effects of both losses to dielectric walls and heat conduction is presented. The interaction of the plasma with dielectric walls is included through three frequencies accounting for ion recombination, energy losses, and near-wall-conductivity. These frequencies depend on the secondary emission of the dielectric walls and the dynamics of the radial plasma flo w. Energy losses, concentrated in the acceleration region, reduce plasma temperatures, near-wall conductivity is marginal, and ion recombination is high in the diffusion region. The main effects of heat conduction are the smoothing on the temperature profile around the ionization region, and a strong restriction to the parametric range where efficient stationary solutions are found.