Tool for simultaneously holding several attachment clips in contact with an aircraft fuselage frame element

Patent metadata

Field	Value
Publication number	US-9789948-B2
Application number	US-201414448807-A
Country	US
Kind code	B2
Filing date	Jul 31, 2014
Priority date	Aug 1, 2013
Publication date	Oct 17, 2017
Grant date	Oct 17, 2017

Abstract

A system with attachment clips designed to fix an attachment element of an aircraft fuselage frame onto a fuselage skin and/or to stiffeners fitted onto this fuselage skin is provided. The system includes tooling elements arranged alternately with the clips such that they connect to each other, in order to reduce the fabrication time and cost of an aircraft fuselage.

First claim

The invention claimed is:

1. A system comprising:
a plurality of attachment clips in a number greater or equal to three, the system being designed to fix an attachment element of an aircraft fuselage frame onto a fuselage skin and/or to one or more fuselage stiffeners fitted onto the fuselage skin; and
junction elements configured as reusable tooling elements arranged alternately with the plurality of attachment clips such that the tooling elements and the plurality of attachment clips connect to each other,
wherein the junction elements are arranged such that the attachment clips are not in contact with each other.

2. The system according to claim 1 , wherein each of at least several of the attachment clips comprise first and second connection devices, each mounted on one of the tooling elements.

3. The system according to claim 2 , wherein at least one of the first and second connection devised is in the form of a tab.

4. The system according to claim 2 , wherein at least one of the first and second connection devices is removable.

5. The system according to claim 4 , wherein at least one of the first and second connection device comprises a mechanically weakened zone, which is breakable in order to separate from a respective one of the plurality of attachment clips.

6. The system according to claim 2 , wherein at least one of the first and second connection devises is designed so that the at least one of the first and second connection devised forms a fastening device for equipment that will be mounted on the aircraft fuselage frame, after a tooling element associated with the at least one of the first and second connection devices has been removed.

7. The system according to claim 1 , wherein the tooling elements are in the form of rods oriented approximately parallel to the longitudinal direction of the system along which these tooling elements and the plurality of attachment clips are placed in sequence.

8. The system according to claim 7 , wherein one end of each of at least several of the rods is mounted to the first connection device of a first of the plurality of attachment clips and another end of each of the several rods is mounted to the second connection device of a second of the plurality of attachment clips, the first and second of the plurality of attachment clips being placed on opposite ends of each of the at least several of the rods.

9. The system according to claim 1 , wherein each of the plurality of attachment clips comprises at least one part shaped like a corner reinforcement.

10. The system according to claim 1 , wherein at least several of the tooling elements and the plurality of attachments clips are connected to each other by flexible connections.

11. The system according to claim 1 , wherein the system comprises between five and fifteen attachment clips.

12. An assembly comprising:
an element of the fuselage frame; and
a system with a plurality of attachment clips being in contact with the element of the fuselage frame,
wherein the system comprises:
the plurality of attachment clips in a number greater or equal to three, the system being designed to fix an attachment element of an aircraft fuselage frame onto a fuselage skin and/or to one or more fuselage stiffeners fitted onto the fuselage skin; and
junction elements configured as reusable tooling elements arranged alternately with the plurality of attachment clips such that the tooling elements and the plurality of attachment clips connect to each other,

wherein the junction elements are arranged such that the attachment clips are not in contact with each other.

13. A method of assembling a plurality of attachment clips onto an element of an aircraft fuselage frame, the method comprising:
fixing the plurality of attachment clips of a system to the element of the aircraft fuselage frame; and
removing reusable tooling elements from the system,
wherein the system comprises:
the plurality of attachment clips in a number greater or equal to three, the system being designed to fix an attachment element of an aircraft fuselage frame onto a fuselage skin and/or to one or more fuselage stiffeners fitted onto the fuselage skin; and
junction elements configured as reusable tooling elements arranged alternately with the plurality of attachment clips such that the tooling elements and the plurality of attachment clips connect to each other,

wherein the junction elements are arranged such that the attachment clips are not in contact with each other.

14. The method according to claim 13 , further comprising using the system when the element of the aircraft fuselage frame is already in position relative to a fuselage skin, or when the element of the aircraft fuselage frame is at a distance from the fuselage skin away from a fuselage segment into which the element of the aircraft fuselage frame is integrated.

15. The method of claim 13 , further comprising:
attaching the plurality of attachment clips to the fuselage skin and/or the one or more fuselage stiffeners.

Assignees

• Airbus Operations Sas

Inventors

• Marin Yannick
• Luche Emilie

Classifications

• B64C1/068

  Fuselage sections · CPC title

• B64F5/10

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

• B64C1/12 Primary

  Construction or attachment of skin panels · CPC title

• B64C1/061

  Frames · CPC title

• Y10T29/4981

  Utilizing transitory attached element or associated separate material · CPC title