Aircraft joint

Patent metadata

Field	Value
Publication number	US-10787241-B2
Application number	US-201715593036-A
Country	US
Kind code	B2
Filing date	May 11, 2017
Priority date	May 11, 2016
Publication date	Sep 29, 2020
Grant date	Sep 29, 2020

Abstract

An aircraft joint between overlapping first and second components includes a fastener assembly. The fastener assembly includes a threaded fastener and a boss having an outer diameter and a threaded internal bore. The boss is fixedly attached to the second component at the overlap region. The first component has a through hole having a diameter sized to receive the outer diameter of the boss. The boss is received in the through hole from a first side of the first component. The fastener extends through the through hole from a second side of the first component opposite the first side. The fastener is threadably received in the internal bore of the boss and reacts against the second side of the first component to fasten the first component to the second component.

First claim

The invention claimed is:

1. An aircraft joint, comprising:
a first component,
a second component overlapping the first component at an overlap region,
and a fastener assembly including
a threaded fastener and
a circular cylindrical boss having an outer diameter and a threaded internal bore, wherein a center axis of the circular cylindrical boss is co-axial with a center axis of the internal bore,
wherein the circular cylindrical boss is fixedly attached to the second component at the overlap region, the first component has a circular through hole having a diameter sized to receive the outer diameter of the circular cylindrical boss, the circular cylindrical boss is received in the circular through hole from a first side of the first component, and the fastener extends through the circular through hole from a second side of the first component opposite the first side, and
the fastener is threadably received in the internal bore of the circular cylindrical boss and reacts against the second side of the first component to fasten the first component to the second component.

2. An aircraft joint according to claim 1 , wherein the first component has an outer aerodynamic surface and the second component has an outer aerodynamic surface.

3. An aircraft joint according to claim 1 , wherein the fastener assembly further comprises a washer which bears against the second side of the first component.

4. An aircraft joint according to claim 3 , wherein the fastener has a head which bears against the washer.

5. An aircraft joint according to claim 1 , wherein the fastener is removable from the boss.

6. An aircraft joint according to claim 1 , wherein the boss is attached to the second component by one or more of bonding, fastening or welding.

7. An aircraft joint according to claim 6 , wherein the boss has an attachment flange and the boss is attached to the second component by the attachment flange.

8. An aircraft joint according to claim 1 , further comprising a plurality of the fastener assemblies.

9. An aircraft joint according to claim 1 , wherein the first component has a joggle comprising a proximal portion, and a distal portion extending substantially parallel with the proximal portion.

10. An aircraft joint according to claim 9 , wherein the fastener includes a shank extending into the distal portion of the first component.

11. An aircraft joint according claim 2 , wherein the fastener assembly constrains movement of the first component relative to the second component in a direction normal to the outer aerodynamic surfaces of first and second components in the vicinity of the fastener assembly.

12. An aircraft joint according to claim 11 , wherein the outer aerodynamic surfaces of the first and second components are substantially, flush across the joint.

13. An aircraft joint according to claim 1 , wherein the first and second components are aircraft wing components.

14. An aircraft joint according to claim 13 , wherein the first and second components are a wing cover and a wing leading edge panel.

15. An aircraft joint according to claim 1 , wherein the first component and the second component are not overlapping outside the overlap region.

Assignees

• Airbus Operations Ltd

Inventors

• Holmes Vernon
• Evans Rodney
• Kosteletos Stefanos

Classifications

• F16B37/061

  by means of welding · CPC title

• F16B5/0642

  the plates being arranged one on top of the other and in full close contact with each other · CPC title

• B64C3/26 Primary

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• 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

• B64C3/28

  Leading or trailing edges attached to primary structures, e.g. forming fixed slots · CPC title