Strain coordination layer for integral forming of ablative thermal protection structure as well as preparation method thereof and application

Abstract

The invention relates to a strain coordination layer which is compounded from a film and a carrier, wherein the film is prepared by a high-temperature-resistant phenolic aldehyde modified epoxy resinsystem; and the carrier is glass fiber fabric, quartz fiber fabric, polyester fiber fabric and the like. The invention further relates to a method for preparing the strain coordination layer, a methodof preparing a cabin from the strain coordination layer and the cabin prepared by the method. The strain coordination layer can realize integral forming and curing of a metal cabin body and an outerheat-resistant layer, is simple in technological process, is short in production period, and is especially suitable for mass production. The strain coordination layer disclosed by the invention can realize thermal deformation and stress matching with the heat-resistant layer / the metal cabin body very well, realizes requirements of high shear strength and high peel strength, prevents the cabin fromrelatively great deformation, avoids heat-resistant layer cracking de-bonding risk, has high impact resistance and damping anti-seismic characteristics, and can be suitable for large-area ablative heat-resistant application of a metal structure surface-layer material of a high-speed aircraft under various complex working conditions.

Description

technical field [0001] The invention relates to a preparation method of an anti-debonding interface coordinating layer for integral molding of an ablation-resistant and heat-proof layer structure and a cabin thereof, belonging to the technical field of functional composite materials. Background technique [0002] Thermal protection materials are generally called ablation materials or ablation heat protection materials. 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 cabin section of the composite structure mainly adopts the split forming scheme: the heat-proof layer is wound and solidified on the winding mandrel, and then machined to ensure the external dimensions; after demoulding, it is then glued to the metal cabin body. The heat-resistant layer is separately formed, the process flow is relatively complicated, the production cycle is long, and the heat-resista...

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

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