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Honeycomb core splicing method

A honeycomb core and honeycomb technology, applied in the field of composite materials, can solve the problems of shortening the molding cycle and long cycle, and achieve the effect of alleviating the mismatch of thermal expansion coefficients

Active Publication Date: 2019-08-09
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The object of the present invention is to propose a honeycomb core splicing method for the problems of long periods when splicing large numbers and types of honeycombs and composite materials, and honeycomb cracking and debonding caused by mismatching thermal expansion coefficients between different materials. Shorten the molding cycle and reduce problems such as honeycomb cracking caused by thermal expansion mismatch

Method used

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Experimental program
Comparison scheme
Effect test

Embodiment 1

[0032] A kind of splicing method of honeycomb core of the present invention, comprises the following steps:

[0033] Step 1: Install the lower panel on the tooling, and place a non-porous isolation film and a porous isolation film on the lower panel successively;

[0034] Step 2: Place all honeycomb and composite components on the lower panel;

[0035] Step 3: inserting cement between honeycombs or between honeycombs and composite components;

[0036] The thickness of the adhesive is not greater than 1 / 2 of the splicing gap of the components, and the number of layers of the adhesive is set to 2 at the splicing interface; The length is L, and the length of the adhesive on the side of the component with a low thermal expansion coefficient is:

[0037] (1)

[0038] in, , are the temperature values ​​of components with high thermal expansion coefficient and low thermal expansion coefficient when the adhesive is curing; with are the thermal expansion coefficients of h...

Embodiment 2

[0042] A honeycomb core splicing method, the key of which is to place a trapezoidal density of styrofoam 7 between spliced ​​different kinds of honeycombs 6, the specific implementation method is:

[0043] Step 1: Place the composite material panel 2 on the tooling 8, place the non-porous isolation film 3 and the porous isolation film 6 successively after positioning;

[0044] Step 2: Place the honeycomb 5 to be spliced ​​on the porous isolation film 6;

[0045] Step 3: Insert foam glue 7 between the honeycombs 5a and 5b. Styrofoam 7 is divided into three layers, and the width of each layer is 1 / 3 of the width of the splicing gap.

[0046] Wherein the bonding interface of the honeycomb 6a is completely laid with a layer of styrofoam 7,

[0047] The cross-section of the styrofoam 7 placed on the glued interface of the honeycomb 5b is as follows: figure 2 As shown, it is divided into three sections, symmetrically arranged, and the section length of the upper section of foam ...

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Abstract

The invention provides a honeycomb core splicing method which comprises an integral splicing method and adhesive trapezoid distribution. According to the integral splicing method, all composite materials and honeycomb components needing to be spliced are placed between an upper panel and a lower panel of composite materials, an adhesive is inserted in the middle, and the composite materials and the honeycomb components are put into a tank at a time to complete hot-pressing curing; the trapezoid density bonding agent refers to setting the density of the bonding agent into corresponding trapezoid distribution according to the thermal expansion coefficient and the interface temperature distribution condition of materials on two sides, so that the problem of honeycomb cracking or deformation caused by splicing interface thermal stress is relieved. For the problems of long period, thermal expansion stress and the like caused when a honeycomb sandwich structure is formed by splicing a largenumber of various kinds of honeycombs and composite materials, the manufacturing period of the honeycomb sandwich structure with the large number of various kinds of honeycombs can be shortened, and the problems of deformation, honeycomb cracking and the like caused by mismatch of thermal expansion coefficients are relieved.

Description

technical field [0001] The invention relates to the field of composite materials, in particular to a honeycomb core splicing method. Background technique [0002] Both honeycomb and composite materials have high specific strength, and the honeycomb sandwich structure formed by honeycomb and composite materials has been widely used in the aerospace field. With the increasing demand for functional diversity of the honeycomb sandwich structure in the aerospace field, the honeycomb sandwich structure is developing towards a larger number and more types of honeycomb and composite material components. [0003] At present, the splicing method of the honeycomb core is mainly centered on the honeycomb, and the composite material, the honeycomb and the honeycomb are spliced ​​with an adhesive, and then solidified at a high temperature to form a new whole. With the whole as the center, the composite material components and the honeycomb are spliced ​​through the adhesive to form a new...

Claims

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Application Information

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IPC IPC(8): B29C65/48B29L31/60
CPCB29C65/4815B29L2031/608
Inventor 吴晓春刘志杰杨晶晶
Owner CHENGDU AIRCRAFT INDUSTRY GROUP