Method of joining components of an aircraft structure

Patent metadata

Field	Value
Publication number	US-12286239-B2
Application number	US-202418414187-A
Country	US
Kind code	B2
Filing date	Jan 16, 2024
Priority date	Nov 9, 2021
Publication date	Apr 29, 2025
Grant date	Apr 29, 2025

Abstract

Two components of an aircraft structure are joined by providing a threaded opening in one of them and supporting an alignment insert in that opening. The alignment insert is used to guide drilling of the second component such that a hole is produced which is aligned with the threaded opening, for instance using an alignment projection which physically guides a drill. The alignment insert may then be removed. A fastener is then inserted through that hole and into the threaded opening, then tightened to form the completed joint.

First claim

The invention claimed is:

1. A method of joining first and second components of an aircraft structure, the method comprising:
providing a threaded opening in the first component;
attaching an alignment insert to the threaded opening before, during or after locating the second component relative to the first component in a required position; then
holding the alignment insert in a stationary position using the threaded opening in the first component, and drilling a hole in the second component in a position determined by the alignment insert; and subsequently
inserting a threaded fastener through the hole in the second component and into the threaded opening, and tightening the fastener to join the first and second components.

2. A method according to claim 1 , wherein said components are parts of a wing assembly.

3. A method according to claim 1 , wherein the step of providing the threaded opening in the first component includes fixing a nut to the first component.

4. A method according to claim 1 , wherein the method further comprises match-drilling the first component and a third component to form holes therein;
the threaded opening is provided in said hole in the first component; and
said fastener is inserted into the threaded opening through said hole in the third component as well as through the hole in the second component.

5. A method according to claim 1 , further comprising attaching an alignment projection to the alignment insert so that the alignment projection can extend through a pilot hole in the second component, the alignment insert guiding the drilling of the second component via the alignment projection.

6. A method according to claim 5 , wherein the alignment insert has a first thread for engaging the threaded opening, and a second thread for engaging the alignment projection, the first and second threads running in opposite directions.

7. A method according to claim 5 , wherein the alignment projection physically guides the drill drilling the hole in the second component.

8. A method according to claim 7 , wherein the drilling of the hole in the second component is performed using a drill which has an annular cutting edge encircling a central bore, the alignment projection being received within the bore of the drill during said drilling.

9. A method according to claim 8 , wherein the alignment projection engages the alignment insert via an alignment projection thread, and the drill rotates in the same direction as the alignment projection thread.

10. A method according to claim 8 , wherein the central bore of the drill and the alignment projection each define respective stop surfaces, the stop surfaces abutting one another after drilling of the second component so as to prevent the drill from over-penetrating.

11. A method according to claim 1 , wherein the drilling of the second component uses a drill comprising an annular cutting edge encircling a non-cutting projection, the non-cutting projection passing through a pilot hole in the second component and being guidingly received in the alignment insert during drilling of the second component.

12. A method according to claim 11 , wherein the non-cutting projection defines a stop surface and the alignment insert or the first component defines another stop surface, the stop surfaces abutting one another after drilling of the second component so as to prevent the drill from over-penetrating.

13. A method according to claim 11 , wherein the non-cutting projection of the drill is axially movable between extended and retracted positions relative to the annular cutting edge, and the non-cutting projection moves from the extended position to the retracted position in the course of drilling of the second component.

14. A method according to claim 1 , wherein the alignment insert supports an optical target structure and drilling of the second component is performed by a drill using a guidance system, the guidance system controlling the path of the drill based on orientation information provided by the optical target structure.

15. A method according to claim 1 , wherein the alignment insert supports a magnet and drilling of the second component is performed by a drill which using a guidance system, the guidance system controlling the path of the drill base on a sensed location of the magnet.

16. A method according to claim 1 , wherein drilling of the second component is performed by orbital drilling.

17. A kit of parts for performing a method according to claim 3 , the kit comprising the nut, the alignment insert and the fastener, the alignment insert and the fastener each having threads configured for engagement with the threaded opening of the nut.

18. An aircraft or part of an aircraft, comprising first and second components joined using the method of claim 1 .

19. An aircraft or part of an aircraft, comprising first and second components joined using the kit of parts according to claim 17 .

20. A method of attaching a first part of an aircraft structure to a second part of an aircraft structure, the method comprising:
providing a female set of threads on the first part;
mounting a drill guide to the female set of threads before, during or after introducing the second part to the first part; then
holding the drill guide in a stationary position using the female set of threads, and drilling a hole in the second part in a position determined by the drill guide; and subsequently
inserting a joining member with a male set of threads into the female set of threads through the hole in the second part, and tightening the joining member to clamp the first and second parts together.

Assignees

• Airbus Operations Ltd

Inventors

• Bate Christopher Alan
• Jones Tim

Classifications

• F16B5/02

  by means of fastening members using screw-thread ({F16B5/0004 takes precedence}; construction of screw-threaded connections F16B25/00 - F16B39/00) · CPC title

• B23P11/00

  Connecting or disconnecting metal parts or objects by metal-working techniques not otherwise provided for  (connecting sheet metal or metal tubes, rods or profiles B21D39/00; riveting B21J; soldering, unsoldering, welding B23K; hand tools for connecting wire or strip B25B25/00; connecting metal parts by adhesives F16B11/00) · CPC title

• B23P2700/01

  Aircraft parts · CPC title

• B23P19/10

  Aligning parts to be fitted together · CPC title

• F16B37/14

  Cap nuts; Nut caps or bolt caps · CPC title