Honeycomb core end surface gridding sizing process method based on adhesive film thermal fracture

Abstract

The invention relates to a honeycomb core end surface gridding sizing process method based on adhesive film thermal fracture. The honeycomb core end surface gridding sizing process method comprises the following steps of: tensioning the end surface of a honeycomb core by designing a special tool; instantly heating the upper surface of the adhesive film which is flat adhered to the end surface of the honeycomb core by adopting a linear type heating device and a heat air blowing device so that the upper surface of the adhesive film is heated to be softened and inwards recessed into a honeycomb core grid under the action of gravity; reversely exerting high-pressure heat air on the adhesive film along the axial direction of the honeycomb core grid so that the adhesive film is expanded, fractured, shrunk and uniformly collected on the end surface of the seamed edge of the honeycomb core grid, and thus the direct transformation of an adhesive from an adhesive film state to a honeycomb gridding state is realized. The honeycomb core end surface gridding sizing process disclosed by the invention realizes the large-area, one-time, uniform and gridding sizing of the end surface of the honeycomb core by carrying out synchronous and horizontal heating/blowing scanning on the honeycomb core/adhesive film and sufficiently utilizing the advantage of uniformity of the surface density of the structural adhesive film and meets the requirements for small chemical state change and uniform physical distribution state of the large-area honeycomb core gridding sizing on the adhesive.

Description

technical field [0001] The invention belongs to the technical field of honeycomb interlayer composite material structure forming technology, and relates to a honeycomb core end surface gridded sizing process based on adhesive film thermal breakage, which is applied to the formation and sizing of honeycomb sandwich structures of spacecraft, mainly for solar wing substrate honeycomb interlayers Structural honeycomb core sizing. Background technique [0002] The honeycomb sandwich structure is a "sandwich" structure formed by bonding two skins and a honeycomb core. It has excellent specific strength, specific stiffness and fatigue resistance. It is widely used in the center bearing tube of spacecraft and solar wings. Primary and secondary load-bearing structures such as base plates and cabin structural plates. [0003] The molding and sizing process of honeycomb sandwich structure can usually be divided into two categories: skin sizing method and honeycomb core sizing method. ...

AI Technical Summary

Problems solved by technology

This method has the following disadvantages: (1) the distribution uniformity of the adhesive on the end face of the honeycomb core wall is poor, resulting in fluctuations in the bonding performance of the sandwich structure; The performance is unfavorable; (3) In order to control the amount of sizing and drying solvent, the process needs to be repeatedly pai

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