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A method for repairing aircraft thrust reverser components by ablative method

An aircraft and component technology, applied in the field of aircraft thrust reverser maintenance

Active Publication Date: 2022-03-08
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

[0005] Generally, the outer cylinder of the reverse thrust sliding door, the C duct and the rear edge of the reverse thrust sliding door are mostly made of carbon 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 repairing aircraft thrust reverser components by ablative method
  • A method for repairing aircraft thrust reverser components by ablative method
  • A method for repairing aircraft thrust reverser components by ablative method

Examples

Experimental program
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Effect test

Embodiment 1

[0024] A method for maintaining the skin of an aircraft reverse thrust translation door outer cylinder by ablation method, comprising the following steps:

[0025] (1) Determine the damaged area of ​​the skin of the outer cylinder of the reverse thrust translation door of the aircraft, and take samples from different thicknesses and structural areas of the damaged area to obtain structurally representative samples;

[0026] According to the skin structure, it is necessary to select enough structurally representative samples in the damage area, and the number of samples is determined by the area and location of the skin damage.

[0027] For example, during the skin repair process of the V2500 reverse thrust translational door outer cylinder, since there is no original production drawing, it is first necessary to determine the fiber direction reference, and choose the direction parallel to the engine axis from front to back as 0°.

[0028] The skin of the outer cylinder of the a...

Embodiment 2

[0054] A kind of adopting ablation method to carry out the method for maintenance of aircraft reverse thrust C duct torque box, comprises the following steps:

[0055] (1) Determine the damage area of ​​the aircraft reverse thrust C duct moment box, take samples from different thicknesses and structural areas of the damage area, and obtain structurally representative samples;

[0056] According to the structure of the aircraft reverse propulsion C-duct moment box, it is necessary to select enough structurally representative samples in the damage area, and the number of samples is determined by the damaged area and location of the aircraft reverse propulsion C-duct moment box.

[0057] In the process of repairing thrust reverser C duct torque box, since there is no original production drawing, it is first necessary to determine the fiber direction reference, and choose the direction parallel to the engine axis from front to back as 0°

[0058]Among them, the aircraft reverse th...

Embodiment 3

[0070] A method for maintaining the rear edge of an aircraft reverse thrust translation door by using an ablation method, comprising the following steps:

[0071] (1) Determine the damage area at the trailing edge of the reverse thrust sliding door, and take samples from different thicknesses and structural areas of the damage area to obtain structurally representative samples;

[0072] According to the structure of the rear edge of the sliding door of the aircraft, it is necessary to select enough structurally representative samples in the damage area, and the number of samples is determined by the area and location of the skin damage.

[0073] In the process of repairing the rear edge of the anti-thrust translation door, since there is no original production drawing, it is first necessary to determine the fiber direction reference, and choose the direction parallel to the engine axis from front to back as 0°.

[0074] The rear edge of the reverse thrust sliding door of the a...

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Abstract

The invention discloses a method for maintaining aircraft reverse thrust parts by ablation method, which comprises the following steps: (1) determining the damaged area of ​​the aircraft reverse thrust part, sampling different thicknesses and structural regions of the damaged area, and obtaining structural representative (2) According to the large difference in temperature resistance between the resin and carbon fiber in the composite material, the resin was burned off by flame ablation method to leave the laminated structure of carbon fiber; (3) The laminated layer was obtained after layer-by-layer stripping and recording Structural information, and measure the position and size of each layer in the laminate structure through the thickness change of the aircraft reverse thrust component; (4) Obtain the laminate drawing of the damaged area of ​​the aircraft reverse thrust component according to the laminate structure information and position dimensions; (5) ) Prepare new composite materials for maintenance according to the layup drawings, and use the new composite materials to repair damaged areas of aircraft thrust reverser components. This method can realize the maintenance of composite damage area of ​​aircraft thrust reverser parts by using new composite materials.

Description

technical field [0001] The invention belongs to the technical field of aircraft maintenance, and in particular relates to a method for maintaining an aircraft thrust reverser component by using an ablation 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. The matrix materials of composite m...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/40B29C73/02
CPCB64F5/40B29C73/02
Inventor 刘小青蔡俊赵海洋伍星
Owner 中国南方航空股份有限公司