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Foam interlayer structure compound material and preparation method thereof

A composite material and sandwich structure technology, applied in the field of foam composite materials, can solve problems such as insufficient strength, high resin content on the surface of laminates, damage, etc., and achieve the effect of improving shear stiffness, excellent mechanical strength, and broadening the application range

Active Publication Date: 2012-03-28
句容市育达实业投资有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the sewing technology has its own defects: the sewing reinforcement technology will form a resin-rich area near the pinhole of the suture near the surface of both ends. The existence of this resin-rich area will cause the resin content on the surface of the laminate to be too high, and the surface is easy to absorb moisture and cause damage. Microcracks are generated and become the initial damage source of failure
[0005] The most widely used Z-Pin reinforcement technology is the X-cor sandwich structure. Although the X-cor sandwich structure has many advantages, it may have insufficient strength when used on aircraft components that require high stiffness and weight, and the core material and surface layer are easy to fall off. lack of

Method used

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  • Foam interlayer structure compound material and preparation method thereof
  • Foam interlayer structure compound material and preparation method thereof
  • Foam interlayer structure compound material and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0021] A foam sandwich structure composite material, see figure 1 , the composite material comprises an upper skin 1, a lower skin 2, a foam core 3 and a pultrusion rod 4, the foam core 3 is arranged between the upper skin 1 and the lower skin 2; One end of a set of pultrusion rods 4 is connected to the upper skin 1, and the other end is connected to the lower skin 2 to form a rice-shaped structure, and there is a connecting upper skin 1 and lower skin between two adjacent rice-shaped structures. 2 of the pultruded rod 4 .

[0022] A kind of its preparation method of foam sandwich structure composite material, comprises following operation:

[0023] The core material selection density is 50kg / m 3 The polymethacrylimide foam, on the special tooling, implants the pin into the foam core in a mixed manner perpendicular to the foam surface and at a certain angle to form a rice-shaped structure, and the implantation density of the pin perpendicular to the foam surface is 5mm× 5mm...

Embodiment 2

[0027] The core material selection density is 50kg / m 3 The polymethacrylimide foam, on the special tooling, the pin and the foam surface are at 45°, and the implantation density is 10mm×10mm. The upper and lower skins are made of glass fiber epoxy fabric prepreg with a single layer thickness of 0.15 mm, and a 3-layer layup is used. It is required that the pin should be embedded in the first layer of layup to ensure a good combination of pin and layup. The vacuum curing process is adopted, and the curing process curve is as follows: figure 2 . After curing and cooling down, the rice-shaped foam sandwich structure composite material is obtained. According to the principle of pin centering and symmetry, the sample size is selected as follows: flat compression sample is 60mm×65mm; shear sample is 60mm×285mm; bending sample It is 60mm×285mm.

[0028] After testing, the compressive modulus is 65.6MPa; the shear strength is 6.87MPa; the bending strength is 255Mpa.

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Abstract

The invention discloses a foam interlayer structure compound material and a preparation method thereof. A foam core material in the compound material is arranged between an upper skin and a lower skin, wherein one ends of one group of pultrusion rods in the foam core material are connected with the upper skin, the other ends of the group of pultrusion rods are connected with the lower skin to form a *-shaped structure, and pultrusion rods for connecting the upper skin and the lower skin are arranged between every two adjacent *-shaped structures. In the interlayer structure compound material, a plurality of pins are arranged in a foam matrix to form a space grid structure, thus the bonding force between the skins and the core material is improved, and because of geometrical features of the grid structure, the performances such as shearing resisting rigidity can be greatly improved. The foam interlayer structure compound material can be applied to aircraft members with high rigidity and weight requirements, such as wallboards, wing surfaces, tail beams and other main load-carrying structures.

Description

technical field [0001] The invention relates to a foam composite material, in particular to a foam sandwich structure composite material and a preparation method thereof. Background technique [0002] Composite sandwich panels with closed-cell rigid foam as the core material have good dimensional stability under heat and good chemical corrosion resistance, so they are widely used in aviation, aerospace and navigation and other fields. The main disadvantage of closed-cell rigid foam is that its stiffness and strength are lower than those of honeycomb core materials (including NOMEX paper honeycomb), so the tensile, compression, shear and bending strength and stiffness of composite sandwich panels using it as core materials Both are lower than honeycomb sandwich panels with the same core material density. At the same time, because there is no transverse reinforcement, the panel and core material are prone to debonding and damage, especially under the action of impact load...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B32B3/26B32B27/06B32B27/04B32B37/00
Inventor 鲁平才阮诗平
Owner 句容市育达实业投资有限公司
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