Device for creating a stiffened region on an outer structure of an aircraft for subsequently providing a service access if required, and method for producing and using such a service access

Patent metadata

Field	Value
Publication number	US-12116145-B2
Application number	US-202318477264-A
Country	US
Kind code	B2
Filing date	Sep 28, 2023
Priority date	Oct 27, 2022
Publication date	Oct 15, 2024
Grant date	Oct 15, 2024

Abstract

A device for creating a stiffened region on an outer structure of an aircraft for subsequently providing a service access if required is disclosed having an outer structure, a reinforcing plate which is mounted in a predetermined installation region on an inner side of the outer structure and forms a contact surface between the reinforcing plate and the outer structure. The reinforcing plate has a through-opening along the surface normal of the contact surface, and a connecting material which connects the reinforcing plate to the outer structure in an edge region of the contact surface by substance-to-substance bonding and/or by interlocking engagement.

First claim

The invention claimed is:

1. A device for creating a stiffened region on an outer structure of an aircraft for subsequently providing a service access if required, the device comprising:
an outer structure;
a reinforcing plate mounted in a predetermined installation region on an inner side of the outer structure and forms a contact surface between the reinforcing plate and the outer structure, wherein the reinforcing plate has a through-opening along the surface normal of the contact surface;
a connecting material which connects the reinforcing plate to the outer structure in an edge region of the contact surface by substance-to-substance bonding and/or by interlocking engagement;
wherein the outer structure has a removable section which has a smaller areal extent than the reinforcing plate; and,
wherein the through-opening has a smaller areal extent than the removable section, so that a first contact region of the contact surface between the reinforcing plate and an edge region of the removable section and a second contact region of the contact surface between the reinforcing plate and a section of the structure that is adjacent to the edge region of the removable section is formed.

2. The device according to claim 1 , further having a separating means for detaching the removable section of the outer structure from the reinforcing plate without leaving any residue, which separating means is provided at least in some portions in the first contact region of the contact surface.

3. The device according to claim 2 , wherein the separating means is in the form of a separating film, a peel ply or a separating agent.

4. The device according to claim 2 , wherein the separating means is formed along the entire edge region of the removable section.

5. The device according to claim 1 , wherein the first contact region is in the form of a support frame for supporting the edge region of the removable section.

6. The device according to claim 1 , wherein the reinforcing plate has at least one of the following materials: a metallic material, in particular aluminium, a ceramics material, a polymer material and a fibre-reinforced composite material, in particular a carbon fibre composite material or a glass fibre composite material.

7. The device according to claim 1 , wherein the reinforcing plate is produced from the same material as the outer structure.

8. The device according to claim 1 , wherein the connecting material contains at least one of the following materials: epoxy resin, cyanoacrylate, acrylate monomers, MS polymers, polyurethane, thermoplastics and silicone.

9. An aircraft having the device according to claim 1 .

10. A method for producing and using a service access for an outer structure of an aircraft, the method (V) comprising:
providing (V 1 ) a device according to claim 1 ; and,
removing (V 2 ) a section of the outer structure along at least part of the contact surface in order to provide the service access, wherein the section has a smaller areal extent than the reinforcing plate.

11. The method according to claim 10 , wherein removing (V 2 ) the section comprises milling the outer structure.

12. The method according to claim 10 , further comprising performing (V 3 ) maintenance and repair work on an item of equipment of the aircraft by means of the service access.

13. The method according to claim 10 , further comprising
closing (V 4 ) the service access by means of the removed section of the outer structure; and
fastening (V 5 ) the removed section of the outer structure to the reinforcing plate.

14. The method according to claim 10 , further comprising sealing (V 6 ) the outer structure by means of a sealing material which is introduced into a gap formed during the removing (V 2 ).

Assignees

• Airbus Defence & Space Gmbh

Inventors

• Meisner Christoph
• Dittrich Kay
• Calomfirescu Mircea
• Brinkmann Sven

Classifications

• B64C1/14

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title

• B64F5/40

  Maintaining or repairing aircraft · CPC title

• B64F5/60

  Testing or inspecting aircraft components or systems · CPC title

• B64F5/10 Primary

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C1/1446 Primary

  Inspection hatches (for engine cowls B64D29/08) · CPC title