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Large area repair of composite aircraft

A composite material and aircraft technology, applied in aircraft maintenance, aircraft parts, ground devices, etc., can solve problems such as time-consuming, high price, and destructive production

Inactive Publication Date: 2013-01-16
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

If a large fuselage section is damaged, removing and replacing the entire barrel section would be cost prohibitive, production disruptive and time consuming

Method used

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  • Large area repair of composite aircraft
  • Large area repair of composite aircraft
  • Large area repair of composite aircraft

Examples

Experimental program
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Embodiment

[0136] A first embodiment is a method for repairing any damaged area of ​​a one-piece composite component of an aircraft, the damaged area covering the skin of the component and the underlying stiffening substructure, the method comprising: producing a composite material for replacing the damaged Design of custom composite replacement siding for the area, including replacement skin and underlying integrated replacement stiffening substructure; and fabrication of composite replacement siding to the design.

[0137] The damaged section may be a one-piece composite barrel section of the fuselage, and may be at least about 90 cm by about 90 cm. Replacement siding can be designed to match the contours of the damaged area.

[0138] Producing the design of the first embodiment may include creating a detailed definition of the panel of the replacement panel and details of the elements used to secure the replacement panel to the section, wherein:

[0139] The fastening element detail ...

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PUM

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Abstract

A randomly damaged area of a one-piece composite component of an aircraft is repaired according to a method herein. The damaged area covers skin and underlying stiffening substructure of the component. The method includes generating a design of a customized composite replacement panel for replacing the damaged area. The design includes replacement skin and underlying co-cured replacement stiffening substructure. The method further includes fabricating the composite replacement panel according to the design.

Description

Background technique [0001] Commercial aircraft can suffer damage from collisions with flocks of birds, ground handling equipment, wreckage, hail and other accidents. These events can create holes and cracks in aircraft skin and cause damage to underlying stiffening structures (eg, fuselage, stiffeners, pads). For example, the nose cockpit section of the aircraft would be damaged from a collision with a flock of birds, the lower section would be damaged from nose gear folding, the mid-section door enclosure would be damaged from a collision with ground handling equipment, and the lower section would be damaged from a collision with ground handling equipment. The rear will be damaged by the tail touching the ground, etc. It is important that damaged aircraft be repaired and brought into service as quickly as possible. Downtime is very expensive for aircraft carriers, as idled aircraft result in lost revenue. [0002] Restoration of prefabricated / panelized aluminum aircraft i...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00
CPCB64F5/0081B29C73/04B29C2073/264B64F5/40Y10T29/4973
Inventor J·L·米勒S·M·斯班赛G·D·奥克斯S·J·达斯特
Owner THE BOEING CO