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Repairing structure with composite repairing piece and method for forming repairing structure

A composite material and patch technology, which is applied in the field of patch repair structure, can solve problems such as environmental sensitivity, low reliability, and high weight gain, and achieve the effects of improving bonding, reducing use risks, and small structural weight gain

Inactive Publication Date: 2015-12-16
刘龙权
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to overcome the disadvantages of low reliability, environmental sensitivity and heavy weight gain of the current composite material bonding repair method, and provide a new composite material structure patch structure and a new method to reduce the size and structure of the patch weight, and improve the reliability and load-carrying capacity of composite repair structures

Method used

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  • Repairing structure with composite repairing piece and method for forming repairing structure
  • Repairing structure with composite repairing piece and method for forming repairing structure
  • Repairing structure with composite repairing piece and method for forming repairing structure

Examples

Experimental program
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Effect test

Embodiment 1

[0039] The pre-cured sheet and the proposed method are used to repair the cracking damage of the epoxy-based carbon fiber reinforced composite structure with a thickness of 4 mm. The steps are as follows:

[0040] (1) Determining the damage area and extent of the composite structure as a cracking damage with a length of 4 mm;

[0041] (2) First remove the adhesive and sealant on the residual repair area, then apply the drilling method to remove the material within the circumscribed circle of the cracking damage, and finally clean the repair area with a vacuum cleaner, then use 180 and 360 grit sandpaper respectively to polish and repair. area, clean the repair area with solvent, and use a heat gun for local heating and drying;

[0042] (3) Prepare composite material pre-cured patch (16 mm in diameter, 2 mm in thickness, tip ratio of 2:1), TESA8432 hot melt adhesive film (diameter of 16mm, 0.2mm thickness) and carbon fiber suture (500mm length, 0.7mm diameter) impregnated with...

Embodiment 2

[0050] Using the prepreg and the proposed method, the internal delamination damage of the epoxy-based carbon fiber reinforced composite structure with a thickness of 6 mm was excavated and repaired, and the steps were as follows:

[0051] (1) It is determined that there is delamination damage at a depth of 3 mm inside the composite structure, and the circumcircle of delamination damage is 8 mm;

[0052] (2) Use a portable pneumatic die milling to cut off the material in the damaged area. The depth of the cut area is 3 mm, the diameter of the bottom is 8 mm, and the slope of the edge is 3:1, then sandpaper is used to obtain a smooth slope, and finally a vacuum cleaner is used. After cleaning the repair area, polish the repair area with 180-grit and 360-grit sandpaper respectively, clean the repair area with solvent, and use a hot air gun for local heating and drying;

[0053] (3) Prepare composite prepregs of different sizes (the smallest prepreg diameter is 8 mm, the largest d...

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Abstract

The invention discloses a repairing structure with a composite repairing piece and a method for forming the repairing structure and belongs to the technology of composite repairing. The repairing structure is composed of a repaired damaged composite structure, the composite repairing piece, glue between the composite repairing piece and the composite structure, and a sewing thread steeped with a cementing compound. Firstly, small holes penetrating through the repairing piece, the damaged composite structure and a glue layer between the repairing piece and the damaged composite structure are machined in a repairing piece repairing part; secondly, the sewing thread steeped with the cementing compound sequentially penetrates into the small holes; lastly, curing is carried out at the regulated temperature and pressure, so that the sewing thread are bonded to the repairing piece around the sewing thread and the damaged composite structure together, and thus the repairing structure with the repairing piece is formed. By means of the repairing structure formed through the method, the influence on the performance in a composite laminated plate face is small, the environmental sensitivity is reduced, and the weight of the structure is slightly increased; in addition, the bonding effect between the composite repairing piece and the repaired structure can be improved, so that the mechanical property and the reliability of the repairing structure with the composite repairing piece are improved, and the use risk of the repaired composite structure is lowered.

Description

technical field [0001] The invention belongs to the field of composite material repair, and in particular relates to a patch repair structure with a suture inserted between the patch and a damaged composite material structure, a method for forming the repair structure, and a repair structure made by applying the method Has high reliability and carrying capacity. Background technique [0002] Resin-based fiber reinforced advanced composite materials have the advantages of high specific strength and specific stiffness, strong designability, good fatigue resistance, good corrosion resistance and easy integral molding, and are widely used in military aircraft, missiles, rockets and satellites. fields, as well as civil fields such as racing cars, ships, high-speed trains, bridges and wind power blades. However, due to its manufacturing process and the characteristics of its use, composite materials are prone to defects and damage. These defects and damages generally include thr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C09J5/06C09J5/02C09J5/00C08J5/12C08L63/00C08K7/06
Inventor 不公告发明人
Owner 刘龙权
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