Optimal design method of square porous thermal protection material

A thermal protection material and optimization design technology, applied in the aerospace field, can solve the problems of ignoring hole and hole interference, ignoring high-order modal scattering, reducing model prediction accuracy, etc., to achieve the effect of improving prediction accuracy

Inactive 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 account the high-order modal scattering caused by the solid wall at the opening, nor the interference between holes, which reduces the prediction accuracy of the model

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

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Embodiment 1

[0059] Such as figure 1 As shown, the optimized design method of the square porous thermal protection material disclosed in this embodiment, the specific implementation steps are as follows:

[0060] Step 1: Define the square micropore shape parameters and background air medium parameters.

[0061] The square porous thermal protection material is such as figure 2 It is composed of multiple square micro-holes distributed regularly. The depth direction of the hole is defined as the y direction. The surface plane of the material perpendicular to the depth direction of the hole is defined as the xz plane. On the xz plane, the side length is 2b regularly distributed with s as the period. , Square micropores with hole depth h. The dimensionless geometric parameter porosity φ is expressed by the above parameters as φ=4b 2 / s 2 , The dimensionless geometric parameter width to depth ratio is Ar, which is expressed by the above parameter as Ar=2b / h. The density of background air is ρ 0 , ...

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Abstract

The invention discloses an optimal design method of a square porous thermal protection material, relates to an optimal design method of a square porous thermal protection material for inhibiting a Mack second modal unstable wave in a boundary layer, and belongs to the field of aerospace. The implementation method comprises the following steps: defining square micropore shape parameters and background air medium parameters; and establishing a sound field model, and determining a sound pressure reflection coefficient in the sound field model. 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 absolute value of the sound pressure reflection coefficient of 0 order and the absolute value of the sound pressure reflection coefficient of 0 order are minimized, square micropore geometric parameters are determined, and the porous thermal protection material meeting the thermal protection purpose is obtained. The optimized porous thermal protection material meeting the thermal protection purpose is applied to the field of thermal protection, so that the optimized square porous thermal protection material effectively avoids the heat flow peak value of a flow transition region, the thermal load in hypersonic incoming flow is kept in the thermal load transition state of a laminar flow region, and finally, the thermal protection purpose is achieved.

Description

Technical field [0001] The invention relates to an optimized design method for a novel square porous thermal protection material, in particular to an optimized design method for a square porous thermal protection material that suppresses unstable waves of 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 has put 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 boundary layer transition. This is because the boundary layer flow regime has a significant impact on the aerodynamic thermal environment of the hypercraft. The aerodynamic heating in the turbulent zone is much greater than the laminar zone. The peak heat flow generally occurs in the transition zone of the flow, and can reach three times the laminar h...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F2111/06G06F2119/08G06F30/17G06F30/20
Inventor 赵瑞张新昕
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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