Enhanced ionization in the cylindrical Hall thruster
Enhanced ionization in the cylindrical Hall thruster
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DOI：
10.1063/1.1585114
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发表时间：
2002-11
影响因子：
3.2
通讯作者：
A. Smirnov;Y. Raitses;N. Fisch
中科院分区：
文献类型：
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作者：
A. Smirnov;Y. Raitses;N. Fisch
传统的环形霍尔推进器不能有效地缩放到低功率。另一种方法，一个圆柱形霍尔推力器与尖型磁场分布，已被调查。一个相对较大的9厘米直径的圆柱形推进器，在300-1000瓦的功率范围内工作，和2.6厘米的小型化圆柱形霍尔推进器，在50-300瓦的功率范围内工作，表现出与传统的环形霍尔推进器的类似大小的性能。与传统的霍尔推进器相比，圆柱形推进器具有非常高的推进剂利用率。在准一维静止推力器模型的框架内进行的数值模拟表明，推进剂利用率的增加似乎不能用等离子体壁损失的减少来定量解释。一个更完整的理论模型，可能包括动力学效应，将是必要的，以解释所观察到的推进剂利用效果。
Conventional annular Hall thrusters do not scale efficiently to low power. An alternative approach, a cylindrical Hall thruster with a cusp-type magnetic field distribution, has been investigated. A relatively large 9-cm-diam version of a cylindrical thruster, operated in 300–1000 W power range, and the 2.6 cm miniaturized cylindrical Hall thruster, operated in the power range 50–300 W, exhibited performance comparable with conventional annular Hall thrusters of the similar size. The cylindrical thrusters have unusually high propellant utilization, compared to conventional Hall thrusters. Numerical simulations, performed within the framework of a quasi-one-dimensional stationary thruster model, show that the increase in the propellant utilization does not appear to be quantitatively explained by a reduction of plasma wall losses. A more complete theoretical model, likely including kinetic effects, will be necessary to explain the observed propellant utilization effect.