Structure temperature analysis method used for semi-closed region of hypersonic aircraft

A hypersonic and aircraft technology, applied in the field of three-dimensional heat transfer analysis, can solve the problems of inability to balance the accuracy and efficiency of three-dimensional heat transfer analysis results, and achieve the effect of accurate structural thermal protection design

Active Publication Date: 2018-07-20
BEIJING AEROSPACE TECH INST
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Problems solved by technology

[0005] The purpose of the present invention is to overcome the deficiencies of the prior art and provide a structural temperature analysis method for the semi-enclosed area of ​​a hypersonic vehicle, w

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  • Structure temperature analysis method used for semi-closed region of hypersonic aircraft

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[0015] Specific embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. In the following description, for purposes of explanation and not limitation, specific details are set forth in order to provide a thorough understanding of the invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.

[0016] It should be noted here that, in order to avoid obscuring the present invention due to unnecessary details, only the device structure and / or processing steps closely related to the solution according to the present invention are shown in the drawings, and the steps related to the present invention are omitted. Invent other details that don't really matter.

[0017] An embodiment of the present invention provides a structural temperature analysis method for a semi-enclosed region of a hypersonic vehicle, whic...

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Abstract

An embodiment of the invention discloses a structure temperature analysis method used for a semi-closed region of a hypersonic aircraft, relates to a structure temperature analysis technology used forthe semi-closed region of the hypersonic aircraft, and solves the problem of not taking precision and efficiency into consideration at the same time for an aerodynamic heating/multi-part radiated interference/three-dimensional heat transfer analysis result of the semi-closed complex interference region. The method comprises the steps of firstly generating an aerodynamic heating grid of a concerned part; carrying out aerodynamic heating analysis by utilizing the aerodynamic heating grid; carrying out convective heat flow analysis under different wall temperatures; obtaining a convective heat flow database under a high wall temperature; generating a three-dimensional heat transfer analysis grid considering convective heat exchange under the high wall temperature and multi-part radiated interference; and finally carrying out three-dimensional heat transfer calculation considering the convective heat exchange under the high wall temperature and the multi-part radiated interference by utilizing the three-dimensional heat transfer analysis grid. The method is mainly used for structure temperature analysis of the semi-closed region of the hypersonic aircraft.

Description

technical field [0001] The invention relates to the technical field of structural temperature analysis of a semi-enclosed area of ​​a hypersonic aircraft, in particular to a three-dimensional heat transfer analysis method for a semi-enclosed area of ​​a hypersonic aircraft considering high wall temperature convective heat transfer and multi-component radiation interference. Background technique [0002] As the shape of hypersonic vehicles becomes more and more complex, the flight Mach number becomes higher and higher, and the thermal environment on the surface of the vehicle becomes more severe. There is not only aerodynamic heating on the surface of high-temperature components in the semi-enclosed complex interference zone, but also mutual radiation between high-temperature components. Reflecting / absorbing energy, the physical process is very complex. Since the temperature of many components in the complex interference area is on the allowable boundary of the material, whic...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20Y02T90/00
Inventor 王飞周丹朱国祥吴宁宁康宏琳罗金玲
Owner BEIJING AEROSPACE TECH INST
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