期刊
AIAA JOURNAL
卷 56, 期 6, 页码 2235-2241出版社
AMER INST AERONAUTICS ASTRONAUTICS
DOI: 10.2514/1.J056641
关键词
-
资金
- National Natural Science Foundation of China [11672039]
The theoretical thrust mechanism of a single dielectric barrier discharge plasma thruster at low pressure is studied. A theoretical thrust model is proposed to establish that the thrust increases to a maximum and then drops steadily as the pressure monotonically increases over a pressure range from 10 to 90 kPa. A formula for revealing the relationships among the pressure, permittivity, dielectric thickness, and operating voltage is derived from the model. This formula shows that a higher operating voltage and smaller ratio of dielectric thickness to permittivity can lead to a higher pressure at the point of maximum thrust. The theoretical results are consistent with the experimental results. The results can be used to determine the optimal operating pressure for a single dielectric barrier discharge thruster.
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