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Strain coordination layer for integrated integral molding of ablation and heat protection structure, preparation method and application thereof

A technology of integral molding and coordinating layers, applied in the direction of chemical instruments and methods, applications, synthetic resin layered products, etc., can solve the problems that cannot meet the heat-proof structure of the adhesive film, the debonding of the heat-proof layer and the metal cabin, and achieve Avoid the risk of cracking and debonding, achieve shear strength and peel strength requirements, and improve impact resistance

Active Publication Date: 2022-07-05
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In engineering technology, J47 epoxy film or 9621 modified nitrile film is often used as the strain coordination layer. It has been verified by the engineering model that these two materials have different degrees of debonding between the heat protection layer and the metal cabin as the interface coordination layer. Can not meet the needs of the film in the heat-proof structure
[0004] Therefore, there is an urgent need for an interface coordination layer suitable for resin-based ablative heat-resistant materials and metal structures to solve the problem of debonding between the heat-resistant layer and the metal cabin during the curing process of the ablative heat-resistant materials

Method used

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  • Strain coordination layer for integrated integral molding of ablation and heat protection structure, preparation method and application thereof
  • Strain coordination layer for integrated integral molding of ablation and heat protection structure, preparation method and application thereof
  • Strain coordination layer for integrated integral molding of ablation and heat protection structure, preparation method and application thereof

Examples

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Embodiment 1

[0057] In this embodiment, the cabin structure is composed of a metal cabin, a strain coordination layer, and an ablation heat protection layer. The material of the metal cabin is 2A12 aluminum alloy, which is formed by a spinning process. The strain coordination layer is a high temperature resistant phenolic modified epoxy resin system (80 parts of barium phenolic resin, 30 parts of bisphenol A epoxy resin and 8 parts of solid nitrile rubber), and the thickness is 0.8mm. The ablation-resistant fiber fabric in the ablation heat protection layer is a high-silica fiber plain fabric, and the ablation-resistant resin is barium phenolic resin. The prepreg tape is made by solution method. The width of the tape is 80mm. , the thickness is 8mm.

[0058] The strain coordination layer is prepared in the following manner: the components used for preparing the high temperature resistant phenolic modified epoxy resin system are stirred at a constant temperature of 120° C. for 3 hours unde...

Embodiment 2

[0068] The method is basically the same as that of Example 1, except that the raw materials used to prepare the high temperature resistant phenolic modified epoxy resin system are 40 parts of barium phenolic resin, 50 parts of bisphenol A epoxy resin and 15 parts of barium phenolic resin. Parts of solid nitrile rubber.

Embodiment 3

[0070] The method is basically the same as that in Example 1, except that the raw materials used for preparing the high temperature resistant phenolic modified epoxy resin system are composed of 120 parts of barium phenolic resin, 10 parts of bisphenol A epoxy resin and 15 parts of phenolic resin. Parts of solid nitrile rubber.

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Abstract

The invention relates to a strain coordination layer, which is composed of a film and a carrier, wherein the film is made of a high temperature resistant phenolic modified epoxy resin system; the carrier is glass fiber fabric, quartz fiber fabric, polyester fiber fabric and the like. The present invention also relates to a method for producing the strain-coordination layer, a method for producing a nacelle using the strain-coordination layer, and a pod produced by the method. The invention can realize the integral molding and curing of the metal cabin and the outer heat-proof layer, has simple technological process and short production period, and is especially suitable for mass production. The strain coordination layer of the present invention can well match the thermal deformation and stress between the heat-proof layer / metal cabin, meet the requirements of high shear strength and peel strength, and avoid large deformation and heat-proof of the cabin. The risk of layer cracking and debonding has high impact resistance and shock absorption and shock resistance. It can be used in large-area ablation and heat protection applications of metal structure surface materials of high-speed aircraft under various complex working conditions.

Description

technical field [0001] The invention relates to a preparation method of an anti-debonding interface coordination layer for integral molding of ablation-resistant and heat-proof layer structure and a cabin thereof, and belongs to the technical field of functional composite materials. Background technique [0002] Thermal protection materials are generally referred to as ablation materials or ablation heat protection materials, and the application of ablation heat protection materials is one of the main uses of composite materials in high-tech fields. At present, the heat-proof layer of the composite structure cabin mainly adopts the split molding scheme: the heat-proof layer is wound and cured on the winding core mold, and then machined to ensure the overall size; after demoulding, it is then glued to the metal cabin body. The heat-proof layer is formed separately, the process flow is relatively complicated, the production cycle is long, and the molding of the heat-proof laye...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B29C70/34B29C70/44B29C70/86B29C70/68B29C70/88B29B15/14B32B15/20B32B15/092B32B15/098B32B27/38B32B27/42B32B27/06B32B27/12B32B27/20B32B27/18B32B17/02B32B27/08B32B17/10B32B33/00B29K705/00B29K705/02B29L31/30
CPCB29C70/342B29C70/443B29C70/865B29C70/683B29C70/88B29B15/14B32B15/20B32B15/092B32B15/098B32B27/38B32B27/42B32B27/06B32B27/12B32B27/20B32B27/18B32B5/02B32B27/08B32B17/10B32B33/00B29K2705/00B29K2705/02B29L2031/3079B29L2031/3097B32B2262/101B32B2307/558B32B2307/304B32B2605/18
Inventor 郝春功夏雨谢永旺李丽英许孔力许学伟王国勇张昊
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH