Multi-channel pulsed arc plasma flow control device and method for promoting boundary layer transition

A technology of pulsed arc and plasma, which is applied in the direction of boundary layer control, aircraft control, and the influence of air flow passing through the surface of the aircraft, etc., which can solve the problems of long pulse interval time, small disturbance area, and inability to generate large-area continuous disturbance. , to increase the size of the disturbance area, promote the transition, and increase the disturbance frequency

Active Publication Date: 2020-11-10
AIR FORCE UNIV PLA
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  • Description
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  • Application Information

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Problems solved by technology

However, the excitation method is mostly single-channel excitation, the disturbance area is small, and the pulse interval is long, so it cannot produce large-area continuous disturbance effect

Method used

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  • Multi-channel pulsed arc plasma flow control device and method for promoting boundary layer transition
  • Multi-channel pulsed arc plasma flow control device and method for promoting boundary layer transition
  • Multi-channel pulsed arc plasma flow control device and method for promoting boundary layer transition

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specific Embodiment

[0067] In this embodiment, the characteristics of boundary layer transition promoted by multi-channel pulsed arc plasma excitation under the condition of supersonic incoming flow (Ma=2) are studied, and the control effect is compared with that of single-channel excitation.

[0068] combine figure 1 and figure 2 , the invention provides a multi-channel pulsed arc plasma excitation flow control device.

[0069] When the supersonic wind tunnel is started, the high-frequency pulse power supply 4 is controlled by the signal delayer, and after the flow field inside the wind tunnel tends to be stable, the high-frequency pulse power supply 4 is triggered to work, and the high-frequency pulse power supply 4 applies pulse voltage to the circuit loop , the voltage is set to 20kV, the discharge frequency is set to 10kHz, the pulse width is 1000ns, and the rising and falling edges are both 50ns.

[0070] In the pulse arc discharge, the first positive electrode 2-1 and the first negative...

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Abstract

The invention provides a multichannel pulse arc plasma flowing control circuit system. The multichannel pulse arc plasma flowing control circuit system comprises a flat plate (1), a discharge electrode (2), an exciting block (3), a high frequency pulse power supply (4) and a cylindrical vertical through hole (5), wherein the cylindrical vertical through hole (5) is machined in the exciting block and used for fixing the electrode. The invention further provides a method for promoting boundary layer transition through multichannel pulse arc plasma exciting. Through the new thinking of multichannel pulse arc plasma exciting, the size of a disturbance region can be effectively increased, the disturbance frequency can be increased, and the transition of a supersonic boundary layer can be promoted.

Description

technical field [0001] The invention relates to a plasma active flow control technology, in particular to a method for promoting supersonic boundary layer transition and a corresponding multi-channel pulsed arc discharge plasma actuator. Background technique [0002] The supersonic boundary layer has a complex pseudo-ordered structure, and its boundary layer flow state can be divided into two types: laminar flow and turbulent flow, and there are huge differences in frictional resistance and thermal conductivity. Supersonic boundary layer research is an important research content in the field of aerospace. Prediction of boundary layer transition and separation positions and related flow control research are of great engineering significance in aircraft drag reduction, suppression of flow separation, and aircraft performance optimization. Taking the inlet of scramjet engine as an example, there are complex shock wave / boundary layer interference problems inside the inlet and th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C21/00
CPCB64C21/00B64C2230/12
Inventor 吴云唐孟潇张志波郭善广金迪梁华甘甜
Owner AIR FORCE UNIV PLA
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