Atmospheric Plasma Thruster: Theory and Concept

Abstract

Dielectric barrier discharge plasma actuators generate a net response force that exhibits potential for thrust applications such as propulsive systems. In this work, an angled actuator in which the exposed and encased electrodes are not parallel has been investigated using direct force measurements and particle image velocimetry. It was shown that the induced force was nonlinearly increased by increasing the angle between the electrodes. In addition, the direction of the upstream component of the ionic wind was changed by varying the electrode angle. Modifying the angle between the electrodes changes the electric field strength in the vicinity of the plasma actuator, thereby changing the response force produced. Analytical calculations were used to compare expected results with results obtained experimentally. Then, using the results obtained experimentally, a plasma thruster was designed as proof of concept for dielectric barrier discharge plasma actuators as propulsive devices.