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High-speed aircraft large-area interlayer heat protection and insulation structure and forming method thereof

A high-speed aircraft and molding method technology, applied in the direction of layered products, fuselage insulation, etc., can solve the problems of limited use, poor bearing performance, low mechanical properties of aerogel composite materials, etc., to avoid damage, process stability, and benefit The effect of promotion and implementation

Active Publication Date: 2013-09-11
北京玻钢院复合材料有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the mechanical properties of airgel composite materials are low, and the load-bearing performance is poor. Simply using airgel composite materials to apply to large-area fuselage parts of high-speed aircraft as a thermal protection structure still cannot meet the requirements of practical applications; so far, there is no The relevant reports of successful examples that can solve the defects of low mechanical properties and poor load-bearing performance of airgel composite materials limit the use of airgel composite materials in high-speed aircraft re-entry thermal protection systems

Method used

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  • High-speed aircraft large-area interlayer heat protection and insulation structure and forming method thereof
  • High-speed aircraft large-area interlayer heat protection and insulation structure and forming method thereof

Examples

Experimental program
Comparison scheme
Effect test

example 1

[0061] The high-speed aircraft has a large-area sandwich anti-heat insulation structure, and the grid rib support layer and the outer skin heat protection layer are made of fiber-reinforced composite materials composed of high-silica fiber yarn, fabric and phenolic resin; among them, the grid rib support layer The thickness of the inner skin is 2mm, the height of the ribs of the grid ribs is 10mm, the cross-sectional width of the ribs is 2mm, the shape of the grid surrounded by the ribs is rectangular, and its area is 100×200mm; the heat insulation layer is made of carbon dioxide Silica airgel composite material, wherein, the thickness of the silica airgel composite material is the same as the rib height of the grid ribs; the thickness of the outer skin heat-proof layer is 5mm.

[0062] The forming method of the above-mentioned sandwich anti-insulation structure, the specific steps are as follows:

[0063] 1) Select high-silica fiber yarn and high-silica fiber fabric as high-t...

example 2

[0070] The interlayer anti-insulation structure and the forming method of the anti-insulation structure of the present invention are similar to Example 1, and the same steps will not be repeated. The differences are:

[0071] The high-temperature-resistant fiber yarn and fabric selected in the grid rib support layer 2 and the outer skin heat-proof layer 4 are all quartz fibers, and the ablation-resistant resin is selected from modified phenolic resin; the thickness of the inner skin in the grid rib support layer 2 is 1mm; the thickness of the outer skin heat-proof layer is 4mm.

[0072] The forming method of the sandwich anti-insulation structure is the same as that of Example 1, and will not be repeated here. The differences are:

[0073] The high-temperature-resistant fiber in step 1) is made of quartz fiber yarn and quartz fiber fabric, and the ablation-resistant resin is selected as a modified phenolic resin as a raw material for standby;

[0074] In step 2), the base o...

example 3

[0080] The interlayer anti-insulation structure and the forming method of the anti-insulation structure of the present invention are similar to Example 1, and the same steps will not be repeated. The differences are:

[0081] The grid rib support layer 2 and the outer skin heat-proof layer 4 are mixed resin composite materials composed of quartz fiber reinforced polysilazane and benzoxazine. The thickness of the inner skin in the grid rib support layer 2 is 3mm. The rib height of the rib is 12mm; the thickness of the outer skin heat-proof layer is 7mm.

[0082] The forming method of the sandwich anti-insulation structure is the same as that of Example 1, and will not be repeated here. The differences are:

[0083] Step 1) Quartz fiber yarn and quartz fiber fabric are selected as medium and high-temperature resistant fibers; mixed polysilazane resins are used as raw materials for ablation-resistant resin;

[0084] In step 2), the base of the metal bearing structure is cleane...

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Abstract

The invention discloses a high-speed aircraft large-area interlayer heat protection and insulation structure and a forming method thereof, belonging to the field of aerospace aircraft surface layer thermal-protection structures. The interlayer heat protection and insulation structure comprises a grid rib support layer, a heat insulation layer and an outer skin heat protection layer which are sequentially laid from bottom to top on the upper surface of a base of a metal supporting structural part, wherein the grid rib support layer is composed of an inner skin and a plurality of grids; the rib height of the grids is 10mm-12mm, and the sectional width of ribs is 2mm; the heat insulation layer is composed of an aerogel composite material laid in the grid rib support layer; the surface of the heat insulation layer is coated with an adhesive, and then an upper skin heat-protection layer is laid on the surface of the heat insulation layer. The heat protection and insulation structure is applicable to a large-area interlayer between the metal base and a surface layer material of a body of a control cabinet, a load cabinet or an instrument cabinet of a high-speed aircraft, and has the properties of ablation resistance, high-temperature airflow scouring resistance, low thermal conduction, light weight and the like, can meet long-time heat protection and insulation requirements, has good application prospect, and is beneficial to popularization and implementation.

Description

technical field [0001] The invention relates to an interlayer heat-proof structure, in particular to a large-area interlayer heat-proof structure suitable for high-speed aircraft and a forming method thereof, belonging to the field of aerospace vehicle surface heat protection structures. Background technique [0002] With the development of the modern aerospace industry, aerospace vehicles maneuver in the atmosphere at high Mach numbers for a long time, and the aerodynamic heating is serious and long-lasting. The surface structure of the aircraft needs to bear not only mechanical loads but also strong thermal loads. Therefore, the structural design of the thermal protection layer with both load-bearing performance is a major trend in structural design in the aerospace field today. [0003] For the large-area fuselage part of the aircraft, heat-resistant structures such as metal and heat-insulating blankets are generally used to form a heat-resistant system to protect the int...

Claims

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Application Information

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IPC IPC(8): B64C1/40B32B3/12B32B5/24B29C69/00
Inventor 谈娟娟胡良全孙超明陈玲飞彭玉刚
Owner 北京玻钢院复合材料有限公司
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