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Air inlet shock wave control device and method based on surface magnetron arc discharge

An arc discharge and control device technology, which is applied to the air inlet, electrical components, charging system, etc. of the turbine/propulsion device to achieve the effects of light weight, improved electrical conductivity, and increased discharge intensity

Inactive Publication Date: 2018-01-30
AIR FORCE UNIV PLA
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  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

[0005] Aiming at the shortcomings and deficiencies of the existing hypersonic inlet flow control technology, the present invention proposes an inlet shock wave control device and method based on surface magnetron arc discharge, so as to improve Performance at Mach number

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  • Air inlet shock wave control device and method based on surface magnetron arc discharge

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Embodiment Construction

[0025] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0026] In describing the present invention, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", " Orientation indicated by rear, left, right, vertical, horizontal, top, bottom, inside, outside, clockwise, counterclockwise, etc. The positional relationship is based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present invention and simplifying the description, rather than ...

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Abstract

The invention provides an air inlet shock wave control device and method based on surface magnetron arc discharge, and relates to the technical field of plasmas and magnetic fluids. The method comprises the steps that 1 a combination discharge mode maintained by high voltage pulse breakdown-low voltage direct current is used to produce an arc discharge plasma on the inner wall of an air inlet; 2 apermanent magnet is arranged on the wall of the air inlet to exert a magnetic field perpendicular to the direction of the wall; and 3 the shock wave angle is increased through the thermal effect of the discharge plasma, and at the same time the Lorentz force decelerating airflow in the reverse flow direction is generated under the action of the magnetic field. In the step 3, the discharge plasmais restrained to enhance the control effect, so that shock waves of the air inlet intersect at a lip mouth again. According to the invention, the working performance of the hypersonic speed air inletat the non-designed Mach number can be effectively improved, and the stable working range of an aircraft is broadened.

Description

technical field [0001] The invention relates to the technical fields of plasma and magnetic fluid, in particular to an inlet shock wave control device and method based on surface magnetron arc discharge. Background technique [0002] The scramjet engine is the core technology of the hypersonic vehicle, which has great military value and potential economic value, and the hypersonic inlet is one of the key components of the scramjet engine. The hypersonic inlet is usually designed for a certain fixed Mach number. When the flight Mach number is greater than the design Mach number, the shock wave will enter the inlet, form a reflected shock wave, and interact with the boundary layer to cause the boundary layer to separate. The performance of the intake port drops sharply, and even causes the intake port to surge and fail to start. [0003] At present, the flow control of the inlet generally adopts the method of mechanical variable geometry and aerodynamic variable geometry flow...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H05H1/48F02C7/04
Inventor 王宇天李益文张百灵陈戈段鹏振
Owner AIR FORCE UNIV PLA
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