Method for repairing defect of large-thickness composite material part

Abstract

The invention relates to a method for repairing the defect of a large-thickness composite material part. The method comprises the following steps: detecting and confirming the defect and the range ofthe composite material part, milling off the defect area, producing a patch having the same layer number from the same material by a technology, milling the patch to reach the defect size, bonding thepart and the milled patch by using an adhesive, performing double-side delayer polishing on the bonding line area, and afresh performing layer repairing and solidification. The method reduces the area to be repaired, reduces the influences on other areas of the part, increases the force bearing strength of the repaired part, reduces the disability rate of part repairing, improves the product quality, and accelerates the product delivery rate.

Description

technical field [0001] The invention belongs to the technical field of repairing composite material parts, and more specifically relates to a method for repairing large-thickness composite material parts with a pre-cured patch using an adhesive as a medium. Background technique [0002] Composite material repair technology is an indispensable means in the field of manufacturing. Composite materials have the advantages of high specific strength and high specific stiffness. Applying them to aircraft structures can significantly reduce the structural weight. During the manufacturing process, circulation and use of composite parts, defects will inevitably occur, and defects should be found in a timely manner. Repair, otherwise it will affect the quality of parts and even the whole product. Composite repairs are important when parts need to be identified and defect areas removed due to application requirements. [0003] After analysis, the traditional repair method of composite...

AI Technical Summary

Problems solved by technology

However, to remove the defects of large-thickness parts, more layers of grinding are required. Because the distance between the grinding layers is generally at least 2cm, the grinding area will be infinitely enlarged, which will affect the assembly drilling area of ​​the parts. Honeycomb core sandwich test board This results in replacing the defect-free honeycomb core during the repair process, and re-drilling after repair, which increases the difficulty of repair; moreover, the more layers removed by grinding, the more likely problems such as excessive grinding and too large grinding area will occur , which increases the chances of parts being scrapped

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