Display apparatus and method for monitoring the structural integrity of a repair location

Patent metadata

Field	Value
Publication number	US-12486049-B2
Application number	US-201917296398-A
Country	US
Kind code	B2
Filing date	Nov 25, 2019
Priority date	Nov 27, 2018
Publication date	Dec 2, 2025
Grant date	Dec 2, 2025

Abstract

An indication device for monitoring the structural integrity of a repair location on a laminate structure, produced from a composite material, of a part of an aircraft outer skin is specified. The indication device has at least one elongate, thin indicator strip. The indicator strip is detachably applied to the outer layer of the laminate structure in the immediate vicinity of the repair location. The indicator strip is designed to indicate a predefined residual strength of an adhesive joint of a repair patch to the surrounding composite material.

First claim

The invention claimed is:

1 . An indication device for monitoring a structural integrity of a repair location on a laminate structure, produced from a composite material, of a part of an aircraft outer skin,
wherein the indication device has at least one elongate, thin indicator strip detachably applied to an outer layer of the laminate structure in an immediate vicinity of the repair location; and wherein the indicator strip is configured to indicate a predefined residual strength of an adhesive joint of a repair patch to the surrounding composite material, wherein the indicator strip has a predefined prestress matched to a target strength to be achieved of the adhesive joint of the repair patch to surrounding composite material, and wherein the indicator strip is applied to the cured adhesive joint by an adhesive.

2 . The indication device as claimed in claim 1 ,
wherein the indicator strip is composed of a metal, a metal alloy or a fiber composite material.

3 . The indication device as claimed in claim 2 ,
wherein the metal comprises aluminum, titanium, steel or an alloy of one of the aforementioned metals.

4 . The indication device as claimed in claim 1 ,
wherein the adhesive joint is brought about by an adhesive film.

5 . The indication device as claimed in claim 1 ,
wherein the adhesive has a higher adhesion than the adhesive film of the adhesive joint for the repair patch.

6 . The indication device as claimed in claim 1 ,
wherein the indicator strip detaches itself at least partially or is configured to be detached when a predefined residual strength of the adhesive joint is reached.

7 . The indication device as claimed in claim 1 ,
wherein the indicator strip has a predefined breaking point or breaking line.

8 . The indication device as claimed in claim 1 ,
wherein the indicator strip is applied to an application region of the adhesive joint extending beyond an extent of the repair location.

9 . The indication device as claimed in claim 1 ,
wherein the indicator strip has a constant thickness of between 0.1 mm and 0.5 mm.

10 . The indication device as claimed in claim 1 ,
wherein the indicator strip has a ratio of length to width in the range of from 1:2 to 1:10.

11 . The indication device as claimed in claim 1 wherein the indicator strip is introduced into a depression of the composite material.

12 . The indication device as claimed in claim 11 ,
wherein the surface of the indicator strip is flush with the surface of the surrounding composite material.

13 . A method for monitoring the structural integrity of a repair location, wherein the repair has been carried out on a laminate structure produced from a composite material, wherein the laminate structure is part of an aircraft outer skin, wherein the laminate structure is subjected to loads during a flight of the aircraft, wherein the method comprises:
(a) applying an adhesive film to a repair location of a base structure of composite material, wherein the adhesive film extends on an outermost layer of composite material of the base structure at least partially beyond the repair location into a region of extent; (b) gluing a repair patch to the adhesive film at the repair location; (c) curing the adhesive joint; and (d) applying an indication device having an indicator strip to the region of extent, wherein the indicator strip is configured to indicate a predefined residual strength of the adhesive joint of the repair patch to the surrounding composite material, wherein the indicator strip has a predefined prestress matched to a target strength to be achieved of the adhesive joint of the repair patch to surrounding composite material, and wherein the indicator strip is applied to the cured adhesive joint by an adhesive.

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Körwien Thomas
• Maier Anton
• Kruse Thomas
• Holtmannspötter Jens

Classifications

• G01N19/04

  Measuring adhesive force between materials, e.g. of sealing tape, of coating · CPC title

• B29C65/8207

  by mechanical methods · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• B64F5/00

  Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for · CPC title

• B29C73/24

  Apparatus or accessories not otherwise provided for · CPC title