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Block partitioning layout method and system for thermal protection structures of complex shape aircraft

A technology of thermal protection structure and layout method, applied in instruments, special data processing applications, electrical digital data processing, etc. low reliability issues

Active Publication Date: 2018-07-27
BEIJING AEROSPACE TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The embodiment of the present application proposes a static analysis model correction method and system to solve the problems of low accuracy of the static analysis model, large error and low reliability when analyzing the static strength safety margin based on the static model
[0004] This application needs to provide a large-area thermal protection structure layout design method and system suitable for hypersonic aircraft with complex shapes, so as to solve the problem that the layout of large-area thermal protection structures for complex aircraft shapes cannot meet the requirements of the aircraft's shape, temperature resistance, heat insulation, and force. / Thermal deformation matching and other use requirements

Method used

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  • Block partitioning layout method and system for thermal protection structures of complex shape aircraft
  • Block partitioning layout method and system for thermal protection structures of complex shape aircraft
  • Block partitioning layout method and system for thermal protection structures of complex shape aircraft

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Embodiment 1

[0064] The processing of the geometric model mainly includes: using the computer-aided design software UG, first establish the overall model of the upper ceramic panel, sandwich layer, lower ceramic panel, adhesive layer, and metal layer. For example, if the overall thickness is 20mm, the geometric model established A single entity with a thickness of 20mm. The outer surface of the above ceramic panel is used as a reference, and the thickness of the upper ceramic panel, the thickness of the upper ceramic panel + sandwich layer, the thickness of the upper ceramic panel + sandwich layer + lower ceramic panel, and the thickness of the upper ceramic panel + sandwich layer + lower ceramic panel + glue Layer thickness. For example: the thickness of the upper ceramic panel is 2mm, the sandwich layer is 13mm, the lower ceramic panel is 1mm, the adhesive layer is 1mm, and the metal layer is 3mm, then the distance between the outer surface of the upper ceramic panel and the offset surfa...

Embodiment 2

[0073] This example provides a block layout scheme for thermal protection structure of aircraft with complex shape, the scheme includes:

[0074] Step 1: Analyze the distribution characteristics of the aircraft's aerodynamic heat and force loads, and calculate the temperature and pressure load distribution of the aircraft. For the area where the temperature does not exceed 1000 ° C and the surface pressure does not exceed 2 MPa, choose the heat insulation tile of the silicon oxide system; for the area where the temperature does not exceed 1200 ℃, the surface pressure does not exceed 3MPa, select the thermal insulation tile of alumina system.

[0075] The second step: carry out the deformation matching test of the unit structure of the flat insulation tile with a typical size (generally 300mm), and obtain the failure strain under normal temperature conditions.

[0076] Step 3: Carry out the first round of block design for the entire aircraft thermal protection structure. For th...

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Abstract

The invention provides a block partitioning layout method for tile-type external thermal protection structures of a complex shape aircraft. According to the method, thermal-mechanical coupling calculation analysis on the thermal protection structures of different sizes is conducted according to the thermal protection structure design and application constraints of the aircraft to obtain the corresponding relationship between thermal protection structure sizes and response, an allowable response value is set by a test means, and the block partitioning layout design of the thermal protection structures of different parts is finally completed. According to the method and the system, the most critical layout application problem of the tile-type thermal protection structures is solved, and an important technical means is provided for a novel thermal protection structure from a principle sample piece to integrated application.

Description

technical field [0001] The present application relates to the field of aircraft performance analysis, in particular to a block layout method and system for a tile-type thermal protection structure. Background technique [0002] At present, the lifting body configuration has become a typical aerodynamic shape of a hypersonic vehicle. While achieving a good lift-to-drag ratio, this aerodynamic shape also brings about an extremely complex shape. At the same time, hypersonic vehicles fly in the atmosphere at high Mach numbers for a long time, and the aerodynamic and thermal environment is harsh. Large areas of the surface of the vehicle are usually protected by lightweight non-ablative ceramic-based heat-resistant structures. For example, some typical aerodynamic surfaces use Rigid ceramic tiles, due to the great brittleness of this type of material, the largest dimension in the plane generally does not exceed 200mm. In response to this demand, the thermal protection scheme of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23
Inventor 宋月娥熊强曹杰李晶马寅魏韩乐张帆
Owner BEIJING AEROSPACE TECH INST
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