Filamentous sliding discharge closed-loop plasma control system and its control method

Abstract

The invention discloses a wire-like sliding discharge closed-loop plasma control system. The wire-like sliding discharge closed-loop plasma control system comprises an electronic scanning valve, an embedded system controller, a wire-like sliding discharge plasma actuator and a power supply system which are sequentially connected, wherein the power supply system is further connected with the electronic scanning valve and the embedded system controller separately. The system disclosed by the invention can achieve the goal of controlling the lateral force of a slender body by influencing the original asymmetric flowing structure of the back part of the slender body. The invention further provides a method for controlling the slender body back asymmetric flow through the wire-like sliding discharge closed-loop plasma control system, the control efficiency of the control rudder surface of a traditional aircraft is improved, and the flight performance of the aircraft is expected to be greatly improved.

Description

technical field [0001] The invention belongs to the technical fields of aerodynamics, plasma physics and flow control, and specifically relates to a filamentous sliding discharge closed-loop plasma control system, and the invention also relates to the filamentary sliding discharge closed-loop plasma control system controlling Symmetric flow method. 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. When the angle of attack of the aircraft increases to a certain range (25° to 50°), the two separated vortices that were originally left-right symmetrical on both sides of the midline of the back of the slender body will suddenly become asymmetrical, and will randomly generate a large lateral force . A large number of studies have shown that...

AI Technical Summary

Problems solved by technology

Due to the single form of the plasma actuator currently used, few control dimensions, small action area, and weak energy to induce boundary layer acceleration, its effective control range is limited to a very narrow flow condition and area.

Once the flow conditions of the slender body aircraft change, the range of the back separation zone or the relative position of the separation vortex will change drastically, and the original quantitative excitation cannot meet the real-time changing control requirements at all, and cannot make appropriate adjustments in a targeted manner. Therefore, there must be a problem of poor environmental adaptability of the flow control means.

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