A Repair Method for Local Damage of Composite Flap

A technology of composite materials and flaps, applied in the field of aircraft repair, can solve problems such as economic loss, increase of aircraft maintenance and use costs, and failure to restore the shape of flaps, etc., to achieve the effect of reducing maintenance and use costs and prolonging the service life

Active Publication Date: 2017-09-12
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] At present, if the aircraft composite flap has a large area of ​​damage with two edges extending inward, since the shape of the flap cannot be restored, the flap has to be scrapped and the flap must be remanufactured, resulting in large economic losses and increased Aircraft maintenance and operating costs

Method used

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  • A Repair Method for Local Damage of Composite Flap
  • A Repair Method for Local Damage of Composite Flap
  • A Repair Method for Local Damage of Composite Flap

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0042] Example 1, the two edges of the flap adjacent to the trailing edge and the wingtip are broken in a large range inwardly, the maximum distance from the broken edge to the back beam is about 30mm, the length of the broken part from the wingtip to the inside of the flap in the span direction is about 300mm, and the total length of the flap is 1200mm ;

[0043] 1. Determine whether the damaged area of ​​the flap is suitable for repair by this method: do delamination and debonding non-destructive testing on the damage of the flap, and according to the test results: the front beam and the rear beam of the flap and the gap between the front beam and the rear beam The area is not damaged; the damaged area is 32mm away from the rear beam in the chord direction, and the damaged length of the damaged area in the wing direction does not exceed 1 / 3 of the length of the flap, and this method can be used to repair;

[0044] 2. Determine the cutting boundary: draw the parallel lines of t...

Embodiment 2

[0052] In Example 2, the two edges of the flap adjacent to the trailing edge and the wing root are broken in a large range inwardly. The distance from the maximum edge of the break to the rear beam is about 30mm. ;

[0053] 1. Determine whether the damaged area of ​​the flap is suitable for repair by this method: do delamination and debonding non-destructive testing on the damage of the flap, and according to the test results: the front beam and the rear beam of the flap and the gap between the front beam and the rear beam The area is not damaged; the damaged area is 28mm away from the rear beam in the chord direction, and the damaged length of the damaged area in the wing direction does not exceed 1 / 3 of the length of the flap, and this method can be used to repair;

[0054] 2. Determine the cutting boundary: make parallel lines between the flap root and the trailing edge respectively. The two parallel lines are the cutting boundary and the inner edge of the cutting area, and...

Embodiment 3

[0062] In Example 3, the two edges of the flap adjacent to the leading edge and the wingtip are broken in a large range inwardly. The distance from the largest edge of the fracture to the front spar is about 30mm. 1200mm;

[0063] 1. Determine whether the damaged area of ​​the flap is suitable for repair by this method: do delamination and debonding non-destructive testing on the damage of the flap, and according to the test results: the front beam and the rear beam of the flap and the gap between the front beam and the rear beam The area is not damaged; the damaged area is 31mm away from the front beam in the chord direction, and the damage length of the damaged area in the wing direction does not exceed 1 / 3 of the length of the flap, and this method can be used to repair;

[0064] 2. Determine the cutting boundary: make parallel lines between the flap tip and the leading edge respectively. The two parallel lines are the cutting boundary and the inner edge of the cutting area...

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Abstract

The invention belongs to aircraft repair technology, and relates to a repair method for partial damage of aircraft composite material flaps. It is characterized in that the repairing steps are as follows: determining whether the damaged area of ​​the flap is suitable for repairing by the method; determining the cutting boundary; cutting off the cutting area; removing paint; manufacturing repair parts; curing; cleaning; bonding the repair parts to the flaps ; Reinforced with dry glass cloth. The invention proposes a repair method for partial damage of aircraft composite material flaps. When the composite material flaps have a relatively large area of ​​damage with two edges extending inward, the flaps can be repaired, the shape of the flaps is restored, and the length of the flaps is extended. The service life of the flaps is extended, and the maintenance and use costs of the aircraft are reduced.

Description

technical field [0001] The invention belongs to aircraft repair technology, and relates to a repair method for partial damage of aircraft composite material flaps. Background technique [0002] At present, if the aircraft composite flap has a large area of ​​damage with two edges extending inward, since the shape of the flap cannot be restored, the flap has to be scrapped and the flap must be remanufactured, resulting in large economic losses and increased Aircraft maintenance and operating costs. Contents of the invention [0003] The purpose of the invention is: propose a kind of repairing method of aircraft composite material flap local damage, so that when composite material flap occurs the damage of larger area that two edges extend inward, flap can be repaired, recovery flap The shape prolongs the service life of the flaps and reduces the maintenance and use costs of the aircraft. [0004] The technical scheme of the present invention is: a kind of repair method of...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/40
Inventor 王乃文王珺曹景斌章强郝钢凝王松
Owner HARBIN
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