Maximum Thrust of Single Dielectric Barrier Discharge Thruster at Low Pressure

Abstract

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.