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Method for maintaining airplane composite material part by adopting coordinate transformation method

A composite material, technology using coordinates, used 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

[0004]Generally, the reverse thrust sliding door outer cylinder, the air intake outer cylinder and the fan cover skin are mostly made of fiber-reinforced resin-based composite materials, and there are also fiber-reinforced materials maintenance problem

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0026] A method for maintaining the skin of an aircraft reverse thrust translation door outer cylinder by using a coordinate transformation method, comprising the following steps:

[0027] (1) Determine the damaged area of ​​the outer cylinder skin of the reverse thrust translation door of the aircraft as the lower edge of the outer skin, and remove the damaged area by grinding. The grinding method is step grinding or slope grinding, and the material of the outer skin is carbon fiber reinforced resin-based composite material;

[0028] (2) Select a point 2 inches away from the edge of the damaged area outside the damaged area of ​​the composite material part of the aircraft as the origin, and based on this origin, establish the first rectangular coordinate system;

[0029] (3) Select the first separation membrane to cover the entire damaged area, and fix the edges of the first separation membrane, each edge of the first separation membrane exceeds each edge of the damaged area b...

Embodiment 2

[0038] A method for maintaining an aircraft fan cover by using a coordinate transformation method, comprising the following steps:

[0039] (1) Determine the damaged area of ​​the aircraft fan cover, and remove the damaged area by grinding. The grinding method is step grinding or slope grinding, and the outer skin material is carbon fiber reinforced resin-based composite material;

[0040] (2) Select a point 3 inches away from the edge of the damaged area outside the damaged area of ​​the composite material part of the aircraft as the origin, and based on this origin, establish the first rectangular coordinate system;

[0041] (3) Select the first separation membrane to cover the entire damaged area, and fix the edges of the first separation membrane, each edge of the first separation membrane exceeds each edge of the damaged area by at least 3 inches, and the origin set up in step (2) is the origin, The same second rectangular coordinate system is established on the first sep...

Embodiment 3

[0050] A method for maintaining the skin of the outer cylinder of an air inlet by using a coordinate transformation method, comprising the following steps:

[0051] (1) Determine the damaged area of ​​the skin of the outer cylinder of the aircraft inlet, and remove the damaged area by grinding. The grinding method is step grinding or slope grinding, and the outer skin material is carbon fiber reinforced resin matrix composite material;

[0052] (2) Select a point 2 inches away from the edge of the damaged area outside the damaged area of ​​the composite material part of the aircraft as the origin, and based on this origin, establish the first rectangular coordinate system;

[0053](3) Select the first separation membrane to cover the entire damaged area, and fix the edges of the first separation membrane, each edge of the first separation membrane exceeds each edge of the damaged area by at least 3 inches, and the origin set up in step (2) is the origin, The same second rectan...

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PUM

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Abstract

The invention discloses a maintenance method of an airplane composite material part, which comprises the following steps: (1) determining a damage area of the airplane composite material part, and removing the damage area; (2) establishing a first rectangular coordinate system outside the damage area; (3) selecting a first separation membrane to cover the whole damage area, establishing the same second rectangular coordinate system on the first separation membrane, and labeling the laying information of the damage area on the first separation membrane; (4) selecting a second separation membrane, and copying the layering information to the second separation membrane; (5) according to the paving layer information of the second separation membrane, cutting the second separation membrane layerby layer according to a ratio of 1:1 to obtain a repair layer; (6) paving repair layers on the surface of the first separation membrane layer by layer, and sticking the repair layers back to the damage area; and (7) removing the first separation membrane, and curing the repair layers. According to the method, a coordinate system conversion method is adopted to determine the positioning and reference of a repaired paving layer after a damaged area is removed, the repaired paving layer for maintenance is prepared, and the repaired paving layer is adopted to maintain the damaged area.

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 using a coordinate transformation method. 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, so that the comprehensive performance of the composite material is better than that of the original constituent materials to meet various requirements. [0003] Fiber reinforc...

Claims

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Application Information

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IPC IPC(8): B29C73/10B29C73/26B64F5/40B29L31/30
CPCB29C73/10B29C73/26B64F5/40B29L2031/3076B29C2073/262
Inventor 卢伟达王荣巍高赛李志歆李荣嘉郭晓晨
Owner 中国南方航空股份有限公司
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