Sliding discharge exciter and plasma flow control method thereof on slender body

Abstract

The invention discloses a sliding discharge exciter which comprises an insulating medium layer, wherein a lower electrode layer is arranged on the lower bottom surface of the insulating medium layer;a first upper electrode, a second upper electrode and a third upper electrode are arranged on the upper surface of the insulating medium layer; the first upper electrode and the third upper electrodeare positioned on two sides of the second upper electrode respectively; a positive pulse high voltage VNP is applied to the second upper electrode; and a direct-current high voltage VDC1 and a direct-current high voltage VDC2 are applied to the first upper electrode and the third upper electrode respectively. The sliding discharge exciter disclosed by the invention can generate stable and uniformlarge-range sliding plasma discharge so as to control an asymmetric vortex structure when the slender body has a large attack angle, and eliminate lateral force. In the slender body plasma flow control method, through pressure measurement, flow display and other measurement means, the evolution characteristics of asymmetric separation flow of the flow around the back of the slender body in different flow states are understood, and the excitation parameters are adjusted as required so as to realize control on the asymmetric vortex of the slender body in a wide flow range.

Description

technical field [0001] The invention belongs to the technical fields of aerodynamics, plasma physics and flow control, and in particular relates to a sliding discharge exciter, and also relates to a plasma flow control method for a slender body by the sliding discharge exciter. Background technique [0002] The head of modern high-performance fighter jets and tactical missiles usually adopts a slender body structure to reduce drag. In order to obtain good maneuverability, it is required to be able to maneuver at high angles of attack or even under stall conditions. However, when the slender body aircraft maneuvers at a large angle of attack, the flow field around it presents a complex multi-vortex flow phenomenon, the parameters of the flow field change rapidly, the separation of the boundary layer, the formation, development and rupture of the vortex, and the formation of the asymmetric vortex The resulting aerodynamic force and moment have strong unsteady and non-linear ch...

AI Technical Summary

Problems solved by technology

When the incoming flow velocity exceeds 30m / s and the attack angle is greater than 50°, the influence of sinusoidal DBD excitation on the asymmetric separation flow becomes very weak and has almost no control effect

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