Bearing/insulating/ablating all-in-one sandwich structure composite material and preparation method thereof

A composite material and sandwich structure technology, applied in the direction of layered products, etc., can solve the problems of affecting the thermal protection effect of the structural layer, poor thermal insulation performance of the structure, and affecting the use effect, etc., and achieve the improvement of interlayer shear strength and integrity Good, the effect of improving production efficiency

Inactive Publication Date: 2009-04-29
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This process method is difficult to introduce a thermal insulation layer between the ablation layer and the structural layer, so that the thermal insulation performance of the overall structure is poor, which affects the thermal protection effect of the structural layer; and the interface performance between the ablation layer and the structural layer is poor, thus affecting its use

Method used

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  • Bearing/insulating/ablating all-in-one sandwich structure composite material and preparation method thereof
  • Bearing/insulating/ablating all-in-one sandwich structure composite material and preparation method thereof
  • Bearing/insulating/ablating all-in-one sandwich structure composite material and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0059] Example 1: Preparation of a bearing / insulation / ablation integrated sandwich structure composite material

[0060] Such as image 3 , 4 Shown, the concrete processing step of preparing composite material of the present invention is as follows:

[0061] Cut out the carrier layer reinforcement c. The reinforcing material used is carbon fiber twill fabric, purchased from Toray Corporation of Japan, the brand is T300 3K, and the average surface density is 200g / m 2 , according to Figure 5 The shape and size of the male mold 25 shown in the figure cut out 10 layers of carbon fiber twill fabrics and lay them sequentially, and the fiber volume content of the reinforcing material is 45%.

[0062] Cut out the insulation material b. The heat insulation layer material used is polyetherimide foam produced by AIREX company in Switzerland, the brand is AIREX R82.80, the thermal conductivity is 0.037W / mk, and the density is 80kg / m 3 , the thickness of the foam is 20mm, and the ed...

Embodiment 2

[0079] Example 2: Application of the present invention to prepare a bearing / insulation / ablation integral composite material structure

[0080] Cut out the carrier layer reinforcement c. The reinforcing material used is carbon fiber plain weave, purchased from Japan Toray Company, the brand is T300 3K, and the average surface density is 200g / m 2 , cut 12 layers of carbon fiber cloth and lay them sequentially, and the fiber volume content of the reinforcing material is 50%.

[0081] Cut out the insulation material b. The heat insulation layer material b used is polymethacrylimide foam from Degussa Company of Germany, the grade is ROHACELL 71XT, the thickness of the foam is 25mm, and the edge of the heat insulation layer b is stronger than the corresponding ablation layer reinforcement material a and The edge of the reinforcement material c of the load-bearing layer shall be 6mm more (see figure 2 , 5 , Dimension "f" shown in 6), after cutting, pave on the reinforcement mate...

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Abstract

A composite material of sandwich structure integrating loading, heat insulation and ablation and the manufacturing method are characterized in that an integrated pre-forming body is acquired by puncture and suture of the reinforcing material of a bearing layer, the reinforcing material of an ablating cover, and a heating insulation layer positioned between the two layers; an epoxy resin system and a phenolic resin system are injected simultaneously into a vacuum-pumped mould, in which the integrated forming body is pre-placed, by two sets of RTM injection systems respectively, then, the reinforcing materials of the bearing layer and the ablating layer are soaked by epoxy resin and phenolic resin respectively; and the composite material of sandwich structure integrating loading, heat insulation and ablation can be obtained by solidified molding after mould filling. The invention has the advantages that the composite material of sandwich structure integrating loading, heat insulation and ablation is put forward and can be integrally formed by one-time operation, the function of the interlayer between every layer of the composite material is enhanced greatly, the integrality is good; the stratifying and peeling of the composite can be reduced effectively, and the products have good designable property and can be widely applied to the structural parts of aerospace which need heating insulation and thermal protection.

Description

technical field [0001] The invention relates to a composite material for aerospace, in particular to a load-bearing / heat-insulation / ablation integrated sandwich structure composite material used for main load-bearing structural parts that can meet the requirements of aerospace ablation and heat insulation and its preparation method, the composite material can be integrally molded at one time. Background technique [0002] When high-performance re-entry vehicles and hypersonic vehicles fly in the atmosphere, the air in front of the vehicle is subjected to strong compression and friction, and most of the kinetic energy is converted into heat energy, causing the temperature of the surrounding air to rise sharply, and the heat energy rapidly to the surface of the aircraft. This heating phenomenon due to the high-speed flight of objects in the atmosphere is called "aerodynamic heating". Different parts of the aircraft have different aerodynamic heating environments. Taking the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B5/00B32B5/06B29C70/00B29C70/36B29C70/54B29K63/00B29K61/04
Inventor 曾竟成尹昌平肖加余刘钧代晓青
Owner NAT UNIV OF DEFENSE TECH
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