Supersonic aircraft wave resistance measurement device based on laser energy deposition resistance reduction

A technology of laser energy and measuring devices, which is applied in the direction of measuring devices, testing of machines/structural components, instruments, etc., can solve problems affecting the aerodynamic performance of aircraft and increasing energy consumption, so as to improve the technical level and engineering application ability, energy consumption Less, realize the effect of non-invasive flow field control and flow field display measurement

Pending Publication Date: 2019-04-12
PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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AI Technical Summary

Problems solved by technology

When the aircraft flies at hypersonic speed, the shock wave resistance can account for more than half of the total resistance of the aircraft, which will seriously affect the aerodynamic performance of the aircraft and increase energy consumption

Method used

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  • Supersonic aircraft wave resistance measurement device based on laser energy deposition resistance reduction
  • Supersonic aircraft wave resistance measurement device based on laser energy deposition resistance reduction
  • Supersonic aircraft wave resistance measurement device based on laser energy deposition resistance reduction

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Embodiment Construction

[0043] The present application is described in detail below in conjunction with the examples, but the present application is not limited to these examples.

[0044] see figure 1 , the supersonic aircraft wave resistance measurement device based on laser energy deposition drag reduction provided by the present application includes a shock tunnel for generating supersonic airflow, a blunt body 5 for simulating a supersonic aircraft and a laser energy loading system

[0045] The blunt body 5 is accommodated in a shock tunnel, and the shock tunnel forms a bow-shaped shock wave at the front end of the blunt body 5;

[0046] The light path passes through the shock tunnel and generates detonation waves at the bow shock;

[0047] A sensor is embedded in the blunt body 5 for detecting the pressure value at the action point of the bow shock wave and the detonation wave.

[0048] In the device provided by the present application, the blunt body 5 only needs to be installed in a manner ...

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Abstract

The invention discloses a supersonic aircraft wave resistance measurement device based on laser energy deposition resistance reduction. The supersonic aircraft wave resistance measurement device basedon laser energy deposition resistance reduction comprises a shock tunnel, a blunt body and a laser energy loading system; the blunt body is contained in the shock tunnel, and the shock tunnel generates bow shock waves at the front end of the blunt body; a light path penetrates through the shock tunnel and generates detonation waves at the bow shock waves; and the blunt body is used for detectingpressure values at acting points of the bow shock waves and the detonation waves. The measurement device has the advantages that the response speed is high, a flow field structure can not be destroyed, and control is flexible.

Description

technical field [0001] The application relates to a wave resistance measuring device for supersonic aircraft based on laser energy deposition and drag reduction, which belongs to the field of main control flow control. Background technique [0002] Hypersonic flight technology is one of the key technologies that the major space powers in the world are actively developing. When the aircraft flies at hypersonic speed, the shock wave resistance can account for more than half of the total resistance of the aircraft, which will seriously affect the aerodynamic performance of the aircraft and increase energy consumption. Therefore, from two aspects of energy saving and improving aircraft performance, drag reduction has become an important problem that cannot be avoided and must be solved. [0003] Energy deposition drag reduction is to inject energy into a specific area at the front end of the aircraft, increase the total pressure loss of incoming flow, change the flow field stru...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M9/06G01M9/04
CPCG01M9/04G01M9/06
Inventor 李倩王殿恺洪延姬赵文涛
Owner PLA PEOPLES LIBERATION ARMY OF CHINA STRATEGIC SUPPORT FORCE AEROSPACE ENG UNIV
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