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External field repair method for debonding fracture of internal honeycomb of composite material

A composite material and repair method technology, which is applied in the repair field of fiber-reinforced resin-based composite materials, can solve problems such as high cost, complicated procedures, and poor pertinence, and achieve the effect of low cost, simple procedure, and low cost

Active Publication Date: 2021-09-21
中国人民解放军61255部队
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the deficiencies of the prior art, the present invention proposes a repair plan and steps for honeycomb debonding and fracture inside the honeycomb sandwich structure composite material, and overcomes the existence of the existing repair plan. high cost, complex procedures, and poor pertinence

Method used

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  • External field repair method for debonding fracture of internal honeycomb of composite material
  • External field repair method for debonding fracture of internal honeycomb of composite material
  • External field repair method for debonding fracture of internal honeycomb of composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] Step 1: Clean the surface of the repaired area, remove all dust from the damaged surface with a lint-free rag, and clean with acetone; use a marking tape to stick out the outline to be repaired to protect the surrounding undamaged area; use 180-grit sandpaper to remove For the surface paint layer within 50mm beyond the repair area, clean the area where the paint layer has been removed with a vacuum cleaner, and then clean it with acetone; be careful not to use chemical paint strippers.

[0041] Step 2: Damage removal, select scalpel, scissors and grinder, and polish off the damaged glass fiber cloth to obtain a smooth area, the area of ​​the damaged area is 200mm×300mm, the lower panel is debonded, and there are 4 broken cracks in the honeycomb ;Clean the repaired area with a vacuum cleaner, clean the repaired surface with acetone, and dry the glued surface with a hot air blower (eg figure 1 shown).

[0042] Step 3: Dehumidification treatment, apply a controlled heat s...

Embodiment 2

[0050] Step 1: Clean the surface of the repaired area, remove all dust from the damaged surface with a lint-free rag, and clean with acetone; use a marking tape to stick out the outline to be repaired to protect the surrounding undamaged area; use 180-grit sandpaper to remove For the paint layer on the surface 45mm beyond the repair area, clean the area where the paint layer has been removed with a vacuum cleaner, and then clean it with acetone; be careful not to use chemical paint strippers.

[0051] Step 2: Damage removal, select scalpel, scissors and grinder, and polish off the damaged glass fiber cloth to obtain a smooth area. The area of ​​the damaged area is 150mm×250mm, and there is a debonding area of ​​50mm×80mm on the lower panel, in which the honeycomb breaks 2 Clean the repair area with a vacuum cleaner, clean the repaired surface with acetone, and dry the glued surface with a hot air blower (such as figure 1 shown).

[0052] Step 3: Dehumidification treatment, ap...

Embodiment 3

[0060] Step 1: Clean the surface of the repaired area, remove all dust from the damaged surface with a lint-free rag, and clean with acetone; use a marking tape to stick out the outline to be repaired to protect the surrounding undamaged area; use 180-grit sandpaper to remove For the surface paint layer exceeding 40mm in the repair area, clean the area where the paint layer was removed with a vacuum cleaner, and then clean it with acetone; be careful not to use chemical paint strippers.

[0061] Step 2: Damage removal, select scalpel, scissors and grinder, and polish off the damaged glass fiber cloth to obtain a smooth area, the damaged area is 100mm×150mm, the debonding area of ​​the lower panel is 50×50mm, and the honeycomb is broken at one place; Clean the repair area with a vacuum cleaner, clean the repaired surface with acetone, and dry the glued surface with a hot air blower (such as figure 1 shown).

[0062] Step 3: Dehumidification treatment, apply a controlled heat s...

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Abstract

The invention discloses an external field repair method for debonding fracture of an internal honeycomb of a composite material. The external field repair method comprises the following steps: S1, removing an upper panel in a honeycomb damage area; S2, injecting epoxy resin into the periphery of a honeycomb fracture area, and blowing the epoxy resin into a lower panel through cold air; gluing the honeycomb fracture area through a mixture of the epoxy resin and a hollow microsphere filler, and completing gluing of the lower panel, a honeycomb structure and the honeycomb fracture area through vacuumizing; and S3, cutting glass fiber cloth according to the shape of the removed honeycomb damage area, manufacturing a patch, and completing the gluing of the patch. According to the method of the invention, the honeycomb debonding fracture in the composite material is repaired through wet-process glue injection, glue joint and layering, the strength and shape requirements can be met, the weight increment of the repaired structure is small, and the original pneumatic shape is kept.

Description

technical field [0001] The invention relates to the repair of fiber-reinforced resin-based composite materials, in particular to the steps and method for repairing internal honeycomb debonding and fracture of honeycomb sandwich structure composite materials. Background technique [0002] As a typical composite lightweight structure, the honeycomb sandwich structure has been widely used in the fields of aerospace and military equipment, and plays a vital role in promoting the lightweight and high performance of the structure. Due to the influence of design, process, man-made, natural aging and other factors, some defects and damages will inevitably occur in the process of manufacturing and using composite materials, resulting in delamination of upper and lower fiber panels and honeycomb breakage. [0003] The composite material structure of modern aircraft is gradually developing in the direction of integration, and it is no longer an economical choice to directly replace the...

Claims

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Application Information

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IPC IPC(8): B29C73/02B29C73/10B29C73/24B29C73/26
CPCB29C73/02B29C73/10B29C73/26B29C73/245B29C73/24B29C2073/262
Inventor 卫新亮张智敏刘毅侯振宇宋刚李稳梅昌松
Owner 中国人民解放军61255部队
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