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Honeycomb sandwich structure part repairing method for reducing structure loss

A technology of honeycomb sandwich structure and parts, which is applied in the field of repair of honeycomb sandwich structure composite materials, can solve problems such as damage, achieve the effect of improving repair strength and simple and reliable implementation

Inactive Publication Date: 2020-04-07
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although this method can completely repair the honeycomb core in the damaged area, it causes great damage to the original normal structural layup. At the same time, grinding the layup and laying up the restored layup puts forward higher requirements for the entire repair cycle, environment, and difficulty. Therefore, it is of great significance and application value for the manufacture of composite sandwich structural parts to develop a process method that can damage the original structure to a lesser extent and reduce the repair complexity and repair cycle.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0017] In order to further illustrate rather than limit the above-mentioned implementation modes of the present invention, the present invention will be further described below in conjunction with examples. All these ideas should be regarded as the contents disclosed in this technology and the protection scope of the present invention.

[0018] The present invention is carried out as follows: first, the surface of the defect area is cleaned, the center point of the defect is confirmed, and a through hole with a radius of R1-2mm is drilled in the center of the defect, and the through hole only needs to go through the structural layer of the repaired area. Then use the L-shaped rotary cutting device to cut and destroy the honeycomb core in the defect area at a full depth to ensure that the honeycomb core in the defect area has been cut and then use the through hole and syringe to inject the potting compound. During the injection process, the L-shaped agitator can be replaced The...

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PUM

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Abstract

The invention provides a honeycomb sandwich structure part repairing method for reducing the structure loss. For the defective area abandoning laying layer gradient grinding link, a through hole withsmaller diameter is directly drilled in the defect center, and then a defective area honeycomb core is subjected to full-depth cutting and breaking treatment by using an L-shaped rotating cutting device; it is ensured that the defective area honeycomb core is cut and broken and then pouring sealant injection / stirring is carried out by using the through hole and an injection device, it is ensured that a defect area cavity is fully filled with the pouring sealant, and then a curing process is executed. Due to the fact that the original surface is restored by curing and polishing, the defective area can be fully filled under the condition that an original structural laying layer is damaged to a small degree, and the repairing target is achieved.

Description

technical field [0001] The invention relates to a repair method for composite material parts, in particular to a repair method for honeycomb sandwich structure composite materials. Background technique [0002] With the increasing application of honeycomb sandwich structure composite parts in the aerospace field, damage to composite parts is inevitable in the manufacturing process and actual use, especially for fuselage skins, beams, etc. that require frequent turnover Large parts are easily damaged due to poor protection during storage and circulation processing, and there are also many defects in the core area after bonding due to defects in the honeycomb core itself. These defects often cause the parts to be unable to continue to be processed and the aircraft to be unable to continue to be used. How to quickly and efficiently repair the defects in the core area of ​​the composite material and restore its strength as much as possible when the autoclave forming process cann...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C73/02B29C73/24B29C73/26
CPCB29C73/02B29C73/24B29C73/26B29C2073/268B29L2031/3076B29L2031/3082B29L2031/3097
Inventor 古尧王建文
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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