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Research system and experimental research method of delayed hypersonic boundary layer transition materials

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

Active Publication Date: 2018-11-20
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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 of delayed hypersonic boundary layer transition materials
  • Research system and experimental research method of delayed hypersonic boundary layer transition materials
  • Research system and experimental research method of delayed hypersonic boundary layer transition materials

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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 delayed hypersonic boundary layer transition materials, 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 used to study the ...

Embodiment 2

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

[0055] Step 1. Apply the research system of delayed hypersonic boundary layer transition materials and combine a flat plate for ultrasonic incident detection to obtain the plate 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 of the delayed hypersonic boundary layer transition material 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 A 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]

[0058] Among them, when the static experiment simulates the same flight height and the ultra...

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 the delayed hypersonic boundary layer transition material 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 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]

[0069] where a is the speed of sound;

[0070] When the research system of the delayed hypersonic boundary layer transition material simulates a certain flying height in step 1, and the sound speed of the ultrasonic wave is a, the power spectral den...

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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 a delayed hypersonic boundary layer transition material, which provides 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 hypersonic bound...

Claims

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Application Information

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Patent Type & Authority Patents(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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