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Wide-domain supersonic inlet passage based on plasma flow control

A supersonic inlet and flow control technology, which is applied to the combustion of the intake port of the power unit, the layout/installation of the power unit, and the power unit on the aircraft, can solve the problem of single research and improve the flow field characteristics and structure. Simple, the effect of reducing the design Mach number

Inactive Publication Date: 2019-04-12
NANJING UNIV OF SCI & TECH
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

However, the research on the variable geometry method is relatively simple, and most of them rely on the mechanical structure to realize the rotation or translation of a certain part of the intake duct, and the deformation method used has certain limitations.

Method used

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  • Wide-domain supersonic inlet passage based on plasma flow control
  • Wide-domain supersonic inlet passage based on plasma flow control
  • Wide-domain supersonic inlet passage based on plasma flow control

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Embodiment Construction

[0018] Below in conjunction with accompanying drawing of description, the present invention will be further described.

[0019] Such as Figure 1-4 As shown, a wide-velocity supersonic inlet based on plasma flow control includes an inlet main body 13 and a fairing 14 arranged outside the rear part of the inlet main body, and the inlet main body 13 and An intake channel is formed between the fairings 14, and a surface arc discharge plasma excitation device 2 is provided at the front end of the main body of the intake channel.

[0020] The front part of the air inlet main body 13 is a curved wall surface 3 of the air inlet.

[0021] Air inlet lip 4 is formed between the front end of cowl 14 and air inlet main body 13, and air inlet throat 7 is formed between the rear part of the front end of air inlet main body 13 and cowling 14, and the rear end of air inlet main body 13 An air inlet isolation section 8 is formed between the cowling 14 and the rear.

[0022] The part of the ...

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Abstract

The invention relates to a wide-domain supersonic inlet passage based on plasma flow control. The wide-domain supersonic inlet passage comprises a main inlet passage body and a radome. A surface arc discharge plasma excitation device is arranged at the front end surface of the main inlet passage body. When the flight Mach number of the inlet passage is greater than a designed Mach number, the surface arc discharge plasma excitation device is started. The surface arc discharge plasma excitation device is capable of generating a high temperature plasma region in an excitation region on the curved wall of the inlet passage to form a virtual profile, thereby enhancing the virtual front edge shock wave and pushing the external pressure shock wave system of the inlet passage compression surfaceto be deflected outward; and thus the external pressure shock wave system of the inlet passage compression surface is sealed again. Therefore, the super-high rated state under the high Mach number isavoided; and the flow field characteristics of the inlet passage under the high Mach number is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft air intakes, in particular to a wide-area supersonic air intake based on plasma flow control. Background technique [0002] Due to the contradiction between the wide Mach number requirement of the hypersonic inlet and its single design point design method, the aerodynamic performance of the hypersonic inlet at non-design points is not ideal. When the flight Mach number is equal to the design Mach number , the shock wave system on the compression surface is sealed, and when the flight Mach number is lower than the design Mach number, the inclination angle of the shock wave system on the compression surface increases, and the incoming flow overflows at the mouth of the inlet port, so that the flow coefficient of the inlet port decreases significantly, and The overflow resistance increases; when the flight Mach number is higher than the design Mach number, the compression surface shock wave system h...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D33/02
CPCB64D33/02B64D2033/026
Inventor 邵庆龄孙波
Owner NANJING UNIV OF SCI & TECH
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