Honeycomb stabilization method for forming large-thickness large-size honeycomb sandwich structure

Abstract

The invention belongs to the technical field of aviation composite material manufacturing, and discloses a honeycomb stabilization method for forming a large-thickness and large-size honeycomb sandwich structure, for a large-thickness honeycomb, when a local stabilization process is adopted, the lateral pressure resistance of the large-thickness honeycomb is enhanced, the overall rigidity is reduced, the stabilized honeycomb keeps certain deformation capacity, and the stability of the large-thickness honeycomb is improved. When a large-thickness honeycomb sandwich structure is formed, the deviation between a honeycomb and a theoretical molded surface of the honeycomb is reduced through honeycomb deformation, so that enough forming pressure is applied to a mold surface skin of the honeycomb sandwich structure. The method solves the problems that the rigidity of a large-thickness and large-size honeycomb is increased after the side pressure resistance of the large-thickness and large-size honeycomb is increased, the edge of the formed honeycomb sandwich structure is whitened due to edge upwarp, namely the porosity is increased due to insufficient pressurization of the film pasting surface of the area, the preparation process level of the large-thickness and large-size honeycomb sandwich structure is improved, and a large practical application value is achieved.

Description

technical field [0001] The invention belongs to the technical field of manufacturing aviation composite materials, and relates to a method for manufacturing a large-thickness honeycomb sandwich structure, in particular to a honeycomb stabilization method for forming a large-thickness and large-size honeycomb sandwich structure. Background technique [0002] The honeycomb sandwich structure is a special composite material structure, which is usually composed of two or more layers of skins (also known as panels) with a layer of lightweight core sandwiched by adhesives at a certain temperature and pressure to form a composite structure. Overall rigid structure. Because the honeycomb sandwich structure has light weight, high specific strength and specific stiffness, it is widely used in the non-bearing structure of the aircraft body. [0003] Aircraft landing gear doors, wing-body fairings, vertical tail panels and other components, due to high strength and rigidity requirement...

AI Technical Summary

Problems solved by technology

This deviation is related to factors such as honeycomb stabilization temperature distribution, stabilization heating rate, resin curing state of prepreg or adhesive film, etc., which cannot be compensated simply by prefabricated mold surface

[0005] The specific performance is that the quality of the good bonding between the honeycomb surface and the mold surface is poor, and there is a certain gap in the middle. When the honeycomb sandwich structure is formed, due to the rigid support of the honeycomb, the skin of the sandwich structure film surface cannot apply sufficient molding pressure. , causing delamination between the skin and the honeycomb, uneven skin surface and increased skin porosity

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