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A method for analysis and calculation of three-dimensional temperature field of ablative heat-proof structure

A technology of three-dimensional temperature and analysis methods, which is applied in calculation, complex mathematical operations, material thermal conductivity, etc., and can solve problems such as complicated extraction and transformation, and lack of accuracy of calculation results

Active Publication Date: 2014-09-10
SHANGHAI INST OF ELECTROMECHANICAL ENG
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Problems solved by technology

Extraction and transformation are very complicated, on the other hand, the accuracy of calculation results is also lacking

Method used

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  • A method for analysis and calculation of three-dimensional temperature field of ablative heat-proof structure
  • A method for analysis and calculation of three-dimensional temperature field of ablative heat-proof structure
  • A method for analysis and calculation of three-dimensional temperature field of ablative heat-proof structure

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Embodiment Construction

[0017] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0021] (1), the governing equations of the carbonized layer and the original layer are shown in formula (1) and formula (2) respectively.

[0022]

[0023]

[0025] On the ablation surface and the pyrolysis surface, the boundary conditions are shown in formula (3) and formula (4) respectively.

[0026]

[0027]

[0030]

[0031] Where x1 and x3 are the thicknesses of the ablation layer, the carbonized layer and the original layer, respectively, which change with time. L is heat-resistant material

[0033]

[0035]

[0036] For the original layer

[0037]

[0038] Using finite difference method to solve equation (6), specifically the second-order precision implicit difference format. in space and time

[0039]

[0040]

[0042] Establish the three-dimensional finite element model of the relevant structural parts of the high-speed aircraft. The finite eleme...

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Abstract

A method for calculating a three-dimensional temperature field of an ablation heat-proof structure relates to a method for calculating the temperature field of a heat protection structure, in particular to the calculation of the temperature field of an ablation heat-proof structure. The invention overcomes the deficiency of the existing heat-proof structure temperature field analysis method, and provides a three-dimensional temperature field analysis method of the ablation heat-proof structure with high calculation accuracy and simple operation. The present invention is mainly realized through the following technical schemes: (1) calculation of one-dimensional transient heat conduction of the ablation heat-proof layer, (2) calculation of three-dimensional transient heat conduction of the structure, (3) temperature of the ablation heat-proof layer and the structure Field coupling calculations. The invention can complete the analysis of the three-dimensional temperature field of the structure of the hypersonic vehicle equipped with an ablation heat-proof layer under the condition of aerodynamic heating, and the calculation result can be used as the temperature boundary condition of the thermoelastic coupling dynamics analysis. The invention can be used in the heat-proof layer structure design of hypersonic aircraft.

Description

A three-dimensional temperature field analysis and calculation method of ablative heat-proof structure Technical field The present invention relates to hypersonic aircraft technical field, be specifically related to a kind of ablation type heat-proof protection for aircraft The temperature field calculation method of the structure. Background technique There is serious aerodynamic heating in hypersonic vehicle, and thermal protection measures are often taken on the surface of aircraft structure apply. Ablative thermal shielding is a widely used form of thermal protection for hypersonic vehicles, which utilizes the Physical and chemical reactions such as melting, pyrolysis, and sublimation occur, which consume heat and consume the material itself. During the ablation process, the temperature change of the heat-resistant material mainly occurs in the direction of the material thickness perpendicular to the aircraft surface. direction, while the variation in the other ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/13G06F17/00G01N25/18
Inventor 许斌杨琼梁史晓鸣杨炳渊唐国安唐晓峰许泉
Owner SHANGHAI INST OF ELECTROMECHANICAL ENG
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