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A method for bonding and repairing aircraft composite parts using a separate double vacuum bag thermoforming process

A composite material and hot pressing technology, applied in the field of aircraft maintenance, to achieve the effect of completely consistent curvature and not easy to deform

Active Publication Date: 2022-07-19
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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  • A method for bonding and repairing aircraft composite parts using a separate double vacuum bag thermoforming process

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

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

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

[0054]The laminated patch is applied to the area of ​​the aircraft composite material to be repaired and there is no crease or crack between the area to be repaired and the laminated patch;

[0055] (2) on the patch layer, a porous separation membrane is evenly spread, 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;

[0057] (3) Evenly spr...

Embodiment 2

[0069] like figure 1 As shown, a method for repairing an aircraft fan cover using a separate double vacuum bag thermoforming process includes the following steps:

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

[0071] (2) on the patch layer, a porous separation membrane is evenly spread, and each edge of the separation membrane is 1 inch larger than the patch layer;

[0072] (3) Evenly spread glass fiber cloth on the upper layer of the perforated separation membrane, and each edge of the glass fiber cloth is 1 inch larger than the perforated separation membrane layer;

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

[0074] (5) A single layer of breathable cotton is eve...

Embodiment 3

[0081] like figure 1 As shown, a method for repairing an aircraft radome using a separate double vacuum bag thermoforming process includes the following steps:

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

[0083] (2) on the patch layer, a porous separation membrane is evenly spread, and each edge of the separation membrane is 1 inch larger than the patch layer;

[0084] (3) Evenly spread glass fiber cloth on the upper layer of the perforated separation membrane, and each edge of the glass fiber cloth is 1 inch larger than the perforated separation membrane layer;

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

[0086] (5) A single layer of breathable cotton is evenly spre...

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PUM

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Abstract

The invention discloses a method for repairing aircraft composite material parts by adopting a separate double vacuum bag hot-pressing forming process, comprising the following steps: (1) Selecting the area to be repaired of the aircraft composite material parts, and laying them with laminated patches (2) A porous separation film, glass fiber cloth, non-porous separation film and breathable cotton are sequentially laid on the laminated patch; (3) tape is laid along the edge of the breathable cotton, and the first vacuum bag is covered, and the first vacuum bag is installed. Valve and vacuum gauge to adjust the pressure; (4) Select a heating blanket, wrap the heating blanket with breathable cotton, and fix the breathable cotton on the first vacuum bag; (5) Lay tape along the edge of the breathable cotton and cover the second vacuum bag , install a second vacuum valve and an adjustable vacuum gauge to adjust the pressure; (6) select a heat compensation instrument, connect a heating blanket, and heat and cure. The method adopts a separate double vacuum bag hot pressing forming process to reduce the interference and influence on the curved shape of the bonding patch, and maintain the radian and curvature of the forming surface.

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 by adopting a separate double vacuum bag hot pressing forming process, in particular to a Method for bonding repair of material parts. Background technique [0002] Materials are the basis for the development of science and technology. As a new type of material developed recently, composite materials have greatly promoted the development of science and technology. The impact on the aerospace industry is particularly pronounced. Composite material is composed of two or more materials with different properties, through physical or chemical methods, macroscopically composed materials with new properties. Various materials complement each other in performance, resulting in a synergistic effect, so that the comprehensive performance of the composite material is better than that of the original materi...

Claims

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Application Information

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Patent Type & Authority Patents(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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