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Repairing method for honeycomb sandwich structure

A technology of honeycomb interlayer and honeycomb, which is applied in the field of aircraft repair or rework, can solve the problems of heavy weight gain of structural parts, affecting the performance of parts, and heavy packing weight, etc., and achieve the effect of reducing structural weight and improving performance

Inactive Publication Date: 2015-12-23
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] When the aircraft honeycomb sandwich structure needs to be maintained and repaired, the defective honeycomb is generally taken out and replaced with 17# packing (ECS2010.10). However, due to the heavy weight of the packing, the weight of the structural parts increases after repair, which affects the use of parts. performance

Method used

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  • Repairing method for honeycomb sandwich structure
  • Repairing method for honeycomb sandwich structure
  • Repairing method for honeycomb sandwich structure

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Embodiment Construction

[0029] Below in conjunction with accompanying drawing and embodiment the present invention will be further described:

[0030] A kind of honeycomb sandwich structure repair method its principle is

[0031] Combine below figure 1 , figure 2 and image 3 , the specific implementation process of the honeycomb sandwich structure repair method of the present invention is further described, and its specific process is as follows:

[0032] Step 1: Removing the layup and damaging the honeycomb

[0033] The ply to remove flat or slightly contoured areas is done using a pneumatic sanding tool with a 60 grit sanding disc, followed by hand sanding with approximately 320 grit sandpaper; after the ply is removed, the honeycomb must be pneumatically sanded until it is close to the underside of the honeycomb 0.5-1mm of the panel. Usually this area is the adhesive film; the remaining honeycomb must be sanded with 150-grit sandpaper or finer by hand or automatically, being careful not to ...

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PUM

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Abstract

The invention belongs to the aircraft maintenance technology, and particularly relates to a repairing method for a honeycomb sandwich structure. The repairing method includes the steps that firstly, a placement layer and a honeycomb at the damaged portion are ground away, and a lower panel can not be damaged; secondly, a new honeycomb is prepared, and the surface of the honeycomb is glued; thirdly, the honeycomb is put in a cavity of the original honeycomb after being processed; and finally, placement layer replacement is carried out according to the original placement layer. Prepreg, glue film and glass cloth can not be spliced but in seamless butt joint. When the repaired structure is a surface concave as shown, the pneumatic outline can be repaired through filler. Raw materials are used for replacing the honeycomb and the placement layer, and the placement layer is repaired through a wet method. The strength design requirement is met, the structural weight after repairing is reduced, and good compatibility can be kept.

Description

technical field [0001] The invention belongs to aircraft repair or rework technology, and specifically relates to a method for repairing a honeycomb sandwich structure, which is only applicable to parts damaged during the manufacturing and assembling process, and not suitable for in-service parts repaired in a repair shop. Background technique [0002] The honeycomb sandwich structure is widely used in aircraft skins and fairings, which can effectively improve stiffness and ensure aerodynamic shape without increasing weight. [0003] When the aircraft honeycomb sandwich structure needs to be maintained and repaired, the defective honeycomb is generally taken out and replaced with 17# packing (ECS2010.10). However, due to the heavy weight of the packing, the weight of the structural parts increases after repair, which affects the use of parts. performance. Therefore, a new repair method is needed to reduce the weight of the repaired structure while meeting the strength desig...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64F5/40
CPCB29C73/10
Inventor 王乃文曹景斌郝钢凝王松章强王珺
Owner HARBIN
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