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Method for adhesion repair on airplane composite material part by adopting separated double-vacuum-bag hot press molding process

A composite material, thermoforming technology, applied in the field of aircraft maintenance

Active Publication Date: 2019-12-03
中国南方航空股份有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Generally, the anti-thrust sliding door outer cylinder, radome and fan cover of the aircraft are all hyperbolic structures, and most of them are made of fiber-reinforced resin-based composite materials, and there are also maintenance problems of fiber-reinforced materials.

Method used

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  • Method for adhesion repair on airplane composite material part by adopting separated double-vacuum-bag hot press molding process

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0052] Such as figure 1 As shown, a method for repairing the skin of the outer cylinder of the reverse thrust translation door of an aircraft using a separate double vacuum bag thermoforming process includes the following steps:

[0053] (1) Determine the bonding area of ​​the skin of the outer cylinder of the reverse thrust translation door of the aircraft as the lower edge of the outer skin, and spread each layer of fiber patches, and the material of the outer skin is a carbon fiber reinforced resin-based composite material;

[0054]Use the laminated patch to pave until there are no wrinkles or cracks between the area to be repaired and the laminated patch of the aircraft composite material part;

[0055] (2) On the patch layer, evenly pave the separation membrane with holes, and each edge of the separation membrane is 1 inch larger than the patch layer;

[0056] The porous separation membrane is a porous high temperature resistant polyethylene film, the same below;

[005...

Embodiment 2

[0069] Such as figure 1 Shown, a kind of method that adopts separate type double-vacuum bag thermocompression forming process to aircraft fan cover is repaired, comprises the following steps:

[0070] (1) Determine the bonding area of ​​the aircraft fan cover, lay out each layer of fiber patches, and the outer skin material is a carbon fiber reinforced resin-based composite material;

[0071] (2) On the patch layer, evenly pave the separation membrane with holes, and each edge of the separation membrane is 1 inch larger than the patch layer;

[0072] (3) Spread glass cloth evenly on the upper layer of the porous separation membrane, and each edge of the glass cloth is 1 inch larger than the porous separation membrane layer;

[0073] (4) Evenly spread the non-porous separation membrane on the upper layer of the glass cloth, and each edge of the non-porous separation film is 1 inch smaller than the glass cloth layer;

[0074] (5) Spread a single layer of breathable cotton even...

Embodiment 3

[0081] Such as figure 1 Shown, a kind of method that adopts separate type double vacuum bag thermocompression forming process to aircraft radome is repaired, comprises the following steps:

[0082] (1) Determine the bonding area of ​​the aircraft radome, lay out each layer of fiber patches, and the outer skin material is a carbon fiber reinforced resin-based composite material;

[0083] (2) On the patch layer, evenly pave the separation membrane with holes, and each edge of the separation membrane is 1 inch larger than the patch layer;

[0084] (3) Spread glass cloth evenly on the upper layer of the porous separation membrane, and each edge of the glass cloth is 1 inch larger than the porous separation membrane layer;

[0085] (4) Evenly spread the non-porous separation membrane on the upper layer of the glass cloth, and each edge of the non-porous separation film is 1 inch smaller than the glass cloth layer;

[0086] (5) Spread a single layer of breathable cotton evenly on ...

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Abstract

The invention discloses a method for repairing an airplane composite material part by adopting a separated double-vacuum-bag hot press molding process, which comprises the following steps of: (1) selecting a to-be-repaired area of the airplane composite material part, and paving a laminated patch; (2) sequentially paving a porous separation membrane, glass wool cloth, a non-porous separation membrane and breathable cotton on the laminated patch; (3) laying an adhesive tape along the edge of the breathable cotton, covering a first vacuum bag, installing a first vacuum valve and a vacuum meter,and adjusting the pressure; (4) selecting a heating blanket, and wrapping the heating blanket with breathable cotton for fixing the breathable cotton on the first vacuum bag; (5) laying an adhesive tape along the edge of the breathable cotton, covering a second vacuum bag, installing a second vacuum valve and an adjustable vacuum meter, and adjusting the pressure; and (6) selecting a hot patchinginstrument, connecting the hot patching instrument with a heating blanket, heating and curing the laminated patch. According to the method, the interference and influence on the curved surface shape of the bonding patch are reduced by adopting a separated double-vacuum-bag hot-press molding process, and the radian and curvature of the molded surface are maintained.

Description

technical field [0001] The invention belongs to the technical field of aircraft maintenance, and in particular relates to a method for maintaining aircraft composite material parts using a separated double vacuum bag thermoforming process, in particular to a method for aircraft composite parts using a separated double vacuum bag thermoforming process. A method of bonding repairs to material parts. Background technique [0002] Materials are the foundation of the development of science and technology. Composite materials, as a large class of new materials developed recently, have greatly promoted the development of science and technology. The impact on the aerospace industry is particularly pronounced. Composite materials are composed of two or more materials with different properties, through physical or chemical methods, macroscopically composed materials with new properties. Various materials learn from each other in terms of performance and produce synergistic effects, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C73/10B29C73/30B29C73/34B64F5/40B29L31/30
CPCB29C73/10B29C73/30B29C73/34B64F5/40B29L2031/3076
Inventor 王威蔡俊邱运朋李志歆侯聪牛旭超
Owner 中国南方航空股份有限公司
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