Preparation method of honeycomb sandwich structure composite material with high-strength cementing performance

A composite material and honeycomb interlayer technology, which is applied in the field of composite materials, can solve problems affecting the bonding performance of honeycomb core composite material panels and core materials, large specific surface area of ​​micro-nano particles, and weakened resin wettability, etc., to achieve large-scale engineering applications Value, high process flexibility, and the effect of improving bonding performance

Pending Publication Date: 2022-02-11
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although the above method can improve the strength of the resin glue, but due to the large specific surface area of ​​the micro-nano particles, they are prone to agglomeration in the resin body. In order to achieve good dispersion, additional process steps are required, thereby increasing the manufacturing cost.
At the same time, the viscosity of the resin system added with micro-nano particle reinforced fillers will increase and the fluidity of the resin will deteriorate, which will also cause the resin to weaken between the panel and the honeycomb wall during the forming process of the honeycomb sandwich structure, and cannot form resin gel nodules of sufficient size. Or the formation of defects inside the gelatinous tumor will affect the bonding performance of the honeycomb core material composite panel and the core material

Method used

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  • Preparation method of honeycomb sandwich structure composite material with high-strength cementing performance

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Experimental program
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Effect test

Embodiment 1

[0039] The solidified ramie plain cloth / epoxy resin composite laminate is selected as the honeycomb sandwich structure panel, the thickness of the panel is 2.5mm, and the size is 200mm×200mm. Both the liquid adhesive and the adhesive film are polyurethane systems, and the epoxy adhesive film is cut into a size of 200mm×200mm. The honeycomb core material is a ramie fiber paper honeycomb, which has a hole side length of 1.83mm, a height of 20mm, and a size of 200mm×200mm. The reinforcing material system is carbon nanotubes.

[0040] Put the liquid adhesive on a flat tray, and weigh 38.4 g of the ramie fiber paper honeycomb before sticking the adhesive. Afterwards, the ends on both sides of the honeycomb wall are respectively immersed in the liquid adhesive, and the depth of immersion is 2 mm. After the end is attached to the adhesive, weigh 42.5g, and evenly sprinkle and fix the carbon nanotubes on the surface of the adhesive at the end of the honeycomb, weighing 43.1g. The p...

Embodiment 2

[0042] Use T300 carbon fiber / epoxy resin unidirectional prepreg tape to form a composite material panel, the thickness of a single layer of unidirectional tape is 0.125mm, and the laying method is: [-45 / 0 / +45 / 90] 2s , the thickness of the panel is 2mm, and the size is 500mm×300mm. Both the liquid adhesive and the adhesive film are epoxy resin systems, and the epoxy adhesive film is cut into a size of 500mm×300mm. The core material of the honeycomb is an aramid paper honeycomb, which has a hole side length of 3.67mm, a height of 25mm, and a size of 500mm×300mm. The reinforcing material system is aramid chopped fiber with a length of 0.4 mm.

[0043] The liquid adhesive is placed in a flat tray, and the weight of the aramid paper honeycomb is weighed to be 2100g before the adhesive is applied. Afterwards, the ends on both sides of the honeycomb wall are respectively immersed in the liquid adhesive, and the depth of immersion is 2 mm. After the end is attached to the adhesive,...

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Abstract

The invention belongs to the technical field of composite materials, and relates to a preparation method of a honeycomb sandwich structure composite material with high-strength cementing performance. According to the method, adhesive layers are prepared at the ends of the two sides of a honeycomb core material, and in-situ fixation of a reinforcing material at the cementing position of a composite panel and a honeycomb wall is achieved. Under the condition of not influencing the flow of the secondary adhesive film or self-adhesive prepreg resin, the purposes of enhancing the strength of the resin bead and improving the process operability in the forming process are achieved. The forming method is simple and convenient to operate, and the obtained product has excellent panel and core material bonding performance and is particularly suitable for meeting the requirements of the aerospace field for a light high-strength honeycomb sandwich structure.

Description

technical field [0001] The invention belongs to the technical field of composite materials, and relates to a preparation method of a honeycomb sandwich structure composite material with high-strength bonding performance. Background technique [0002] As a lightweight and high-strength composite structure, honeycomb sandwich composites have been widely used in the aerospace field. The bonding performance between the honeycomb core material and the panel is the key factor to determine the mechanical properties of the sandwich structure. There are mainly two modes of bonding between the honeycomb core material and the panel: self-adhesive and secondary transfer. For self-adhesive, it usually depends on the curing molding process, the molten extruded resin in the uncured prepreg blank of the panel forms a resin glue on the wall of the end wall of the honeycomb and the junction of the panel, so as to realize the curing of the composite panel of the honeycomb sandwich structure. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B37/12B32B38/00B32B37/06B32B37/10
CPCB32B37/1284B32B38/00B32B37/06B32B37/10B32B37/1018B32B2038/0076
Inventor 马绪强钱黄海董慧民王永梅李跃腾
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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