Comparison of Simulated Plasma Flow Field in a Two-Dimensional Magnetoplasmadynamic Thruster With Experimental Data
Comparison of Simulated Plasma Flow Field in a Two-Dimensional Magnetoplasmadynamic Thruster With Experimental Data
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DOI：
10.1109/tps.2009.2032913
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发表时间：
2009-12
影响因子：
1.5
通讯作者：
K. Kubota;I. Funaki;Yoshihiro Okuno
中科院分区：
文献类型：
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作者：
K. Kubota;I. Funaki;Yoshihiro Okuno
对100千瓦级二维磁等离子体动力推力器等离子体流场的数值模拟结果与实验数据进行了比较。推进剂为1.25 g/s的氩气，放电电流在8 - 12 kA之间变化。物理模型包括氩离子的非平衡单能级电离和碰撞辐射模型，以详细描述反应过程。我们主要比较的数据是电流路径、电子数密度和电子温度。除电子温度外，计算结果与实验结果定性一致。为了解释电子温度的不一致性，我们从4s和4p态的激发态离子的分布来估计激发温度，实验中用4s和4p态离子的辐射来确定电子温度。结果表明，计算的激发温度与实测结果接近，等离子体偏离了阳极表面附近的局部热力学平衡。关于推力和推力效率，它们对放电电流的变化的特征被很好地捕捉到的模拟，虽然他们是稍微高估与测量值相比。
Comprehensive comparisons of the numerically simulated results of plasma flow fields in a 100-kW-class 2-D magnetoplasmadynamic thruster with the available experimental data are conducted. The propellant is argon of 1.25 g/s, and the discharge current is varied from 8 to 12 kA. The physical model includes a nonequilibrium single level of ionization and a collisional radiative model for argon ion to assess the reaction processes in detail. The data we mainly compared are the current path, electron number density, and electron temperature. There is qualitative agreement between the calculated and experimental results except for the electron temperature. In order to explain the disagreement of the electron temperature, we estimate the excitation temperature from the distributions of the excited ions in 4s and 4p states, the radiation of which was employed to determine the electron temperature in the experiment. As a result, it is found that the calculated excitation temperature becomes close to the measured result and that the plasma deviates from the partial local thermodynamic equilibrium near the anode surface. Regarding the thrust and thrust efficiency, their features against variation of the discharge current are well captured by the simulation, although they are slightly overestimated compared with the measured values.