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Research system and experimental research method for delaying transition of high-supersonic-velocity boundary layer material

A hypersonic, research system technology, applied in the research system and experimental research field of delayed hypersonic boundary layer material transition, can solve the problem that the acoustic resonance mode has not been experimentally verified.

Active Publication Date: 2016-11-16
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Currently, the existence of acoustic resonance modes has not been experimentally verified

Method used

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  • Research system and experimental research method for delaying transition of high-supersonic-velocity boundary layer material
  • Research system and experimental research method for delaying transition of high-supersonic-velocity boundary layer material
  • Research system and experimental research method for delaying transition of high-supersonic-velocity boundary layer material

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0045] Such as figure 1 As shown, the present invention provides a research system for delaying the transition of hypersonic boundary layer materials, which is characterized in that it includes:

[0046] Ultrasonic absorbing layer model 1, it is a plate body, and the upper end surface of plate body is provided with a plurality of rectangular opening grooves 2 that are evenly spaced apart from each other and arranged in parallel; side, so that the ultrasonic waves emitted by the ultrasonic generator are reflected by the ultrasonic absorbing layer to generate echoes; and the pressure sensor 4 is arranged on the other side of the ultrasonic absorbing layer model for receiving echoes.

[0047] In the above scheme, the ultrasonic wave emitted by the ultrasonic generator is used to simulate the second mode wave, which is incident on the ultrasonic absorbing layer model, and the echo is detected by the pressure sensor, and the ultrasonic reflection coefficient is analyzed, which is u...

Embodiment 2

[0054] An experimental research method for delaying the transition of a hypersonic boundary layer material, characterized in that it comprises the following steps:

[0055] Step 1. Apply the research system for delaying the transition of hypersonic boundary layer materials and combine a flat plate for ultrasonic incident detection to obtain the flat ultrasonic echo amplitude A FP , wherein, the specification of the flat plate is 80-100mm×80-100mm×10-20mm;

[0056] Step 2. Apply the research system for delaying the transition of hypersonic boundary layer materials and combine the reference ultrasonic absorbing layer model, ultrasonic absorbing layer model P1 and ultrasonic absorbing layer model P2 to detect and obtain the reference ultrasonic echo amplitude R UAC 、A UACP1 and A UACP2 , using the following formula M to calculate the reflection coefficient as R UAC , R UACP1 and R UACP2 :

[0057] R U A ...

Embodiment 3

[0065] A method for capturing an acoustic resonance mode in a hypersonic boundary layer material, further comprising the following steps:

[0066] Step 1. Apply the research system of delayed hypersonic boundary layer material transition and use the reference ultrasonic absorbing layer model to detect the echo pressure signal, perform Fourier transform on the echo pressure signal, and obtain the corresponding power spectral density feature;

[0067] Step 2. Acoustic resonance mode wavelength λ res It is determined by the channel spacing of two adjacent rectangular open slots among the multiple rectangular open slots, λ res = s; therefore, the acoustic resonance modal frequency f res Obtained by the following formula:

[0068] f r e s = a λ r e s

[0069] where...

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Abstract

The present invention discloses a research system for delaying transition of high-supersonic-velocity boundary layer material, comprising: an ultrasonic absorption layer model; an ultrasonic generator arranged on one side of the ultrasonic absorption layer model; and a pressure sensor arranged on the other side of the ultrasonic absorption layer model for receiving echoes. The invention also discloses an experimental research method for delaying transition of high-supersonic-velocity boundary layer material, and the method enables effective application of the research system for delaying transition of high-supersonic-velocity boundary layer material to carry out research on the impact of ultrasonic absorption layer geometry upon wave absorption characteristics of the material; the invention also provides a method for capturing acoustic resonance mode in the high-supersonic-velocity boundary layer material, and the method is used for validating existence of the acoustic resonance mode to to provide comprehensive experimental support and scientific basis for the design of ultrasonic absorption layers.

Description

technical field [0001] The invention relates to a research system and an experimental research method for delaying the transition of a hypersonic boundary layer material, which provide comprehensive experimental support and scientific basis for the design of the material. Background technique [0002] During hypersonic flight, the boundary layer transition greatly increases the thermal conductivity and frictional resistance of the boundary layer. If the transition of the boundary layer can be delayed, the weight and complexity of the thermal protection system of a hypersonic vehicle can be significantly reduced. In a two-dimensional or quasi-two-dimensional hypersonic boundary layer, the second mode becomes the main unstable mode, that is, the Mack mode. The second mode wave, caused by strong pressure and temperature fluctuations much larger than the velocity fluctuations, is ultrasonic waves trapped in the boundary layer. At present, the main ways to control the hypersoni...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N29/04G01N29/12G01N29/34
CPCG01N29/04G01N29/041G01N29/12G01N29/34G01N2291/014G01N2291/0231
Inventor 吕鹏宫建张玉东
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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