Optimal design method of circular porous thermal protection material

A thermal protection material and optimized design technology, applied in the aerospace field, can solve problems such as not taking into account high-order modal scattering, not taking into account hole-to-hole interference, and reducing model prediction accuracy

Active Publication Date: 2019-08-16
BEIJING INSTITUTE OF TECHNOLOGYGY
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Problems solved by technology

It should be pointed out that the above theoretical models are derived based on the acoustic characteristics of a single hole, and do not take into accoun...

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  • Optimal design method of circular porous thermal protection material
  • Optimal design method of circular porous thermal protection material
  • Optimal design method of circular porous thermal protection material

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Embodiment 1

[0058] Such as figure 1 As shown, the optimal design method of the circular porous thermal protection material disclosed in this embodiment, the specific implementation steps are as follows:

[0059] Step 1: Define the shape parameters of the circular micropore and the parameters of the background air medium.

[0060] figure 2 The circular porous thermal protection material applied on the surface of a hypersonic vehicle, such as image 3 , is composed of a number of circular micro-holes regularly distributed periodically, the y-direction is defined as the pore depth direction, and the material surface plane perpendicular to the pore-depth direction is defined as the xz plane, and the radius is regularly distributed on the xz plane with s as the period b. A circular micropore with a hole depth of h. The dimensionless geometric parameter porosity φ is expressed by the above parameters as φ=πb 2 / s 2 , the dimensionless geometric parameter aspect ratio Ar is expressed as Ar...

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Abstract

The invention discloses an optimal design method of a circular porous thermal protection material, relates to an optimal design method of a circular porous thermal protection material for inhibiting aMack second modal unstable wave in a boundary layer, and belongs to the field of aerospace. The implementation method comprises the following steps: defining a circular micropore shape parameter anda background air medium parameter; and establishing a sound field model, and determining a sound pressure reflection coefficient in the sound field model, wherein the sound field model comprises an incident wave model, a reflected wave model and an in-hole wave model. And through optimization of a numerical method, the sound pressure reflection coefficient |R00| of 0,0 order is minimized, circularmicropore geometric parameters are determined, and the porous thermal protection material meeting the thermal protection purpose is obtained. The optimized porous thermal protection material meetingthe thermal protection purpose is applied to the field of thermal protection, so that the optimized circular porous thermal protection material effectively avoids the heat flow peak value of a flow transition area, the thermal load in hypersonic incoming flow is kept in the thermal load transition state of a laminar flow area, and the thermal protection purpose is achieved.

Description

technical field [0001] The invention relates to an optimal design method for a novel circular porous thermal protection material, in particular to an optimal design method for a circular porous thermal protection material that suppresses unstable waves of the Mack second mode in a boundary layer, and belongs to the field of aerospace. Background technique [0002] With the vigorous development of the aerospace industry, it puts forward higher and higher requirements for the thermal protection of high-speed aircraft. One of the main technical ideas for thermal protection is to reduce the thermal load of the aircraft by suppressing the transition of the boundary layer. This is because the flow state of the boundary layer has a significant impact on the aerodynamic and thermal environment of the hypervehicle. The aerodynamic heating in the turbulent flow area is much greater than that in the laminar flow area. The heat flow peak generally appears in the flow transition zone, wh...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F2119/08G06F30/17G06F30/20
Inventor 赵瑞张新昕
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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