Wing assembly tension joint and method of assembly

Patent metadata

Field	Value
Publication number	US-11370525-B2
Application number	US-201916572968-A
Country	US
Kind code	B2
Filing date	Sep 17, 2019
Priority date	Sep 19, 2018
Publication date	Jun 28, 2022
Grant date	Jun 28, 2022

Abstract

A wing assembly is disclosed. The wing assembly includes a main structure having a first contact face and a first recess arranged to receive a portion of a tension bolt; and a modular edge having a second contact face and a second recess arranged to receive a portion of the tension bolt. The modular edge is pivotally mounted on the main structure for rotation between an installation position and an operational position in which the modular edge is aligned with the main structure to form at least part of an edge of the wing assembly. The wing assembly is arranged such that, when the modular edge is in the operational position, tension in a tension bolt received in the first and second recesses acts to press the first and second contact faces together, thereby forming a tension joint that resists pivoting of the modular edge relative to the main structure.

First claim

The invention claimed is:

1. A wing assembly, the wing assembly comprising:
a main structure comprising a first contact face and a first recess arranged to receive a portion of a tension bolt; and
a modular edge comprising a second contact face and a second recess arranged to receive a portion of the tension bolt, the modular edge being pivotally mounted on the main structure for rotation solely about a stationary rotational axis between an installation position, in which the first and second contact faces are spaced apart, and an operational position, in which the first and second contact faces are abutting and the modular edge is aligned with the main structure to form at least part of an edge of the wing assembly, wherein the modular edge is aligned with the main structure to form at least part of the leading edge or trailing edge of the wing when the modular edge is in the operational position; and wherein:
the wing assembly is arranged such that, when the modular edge is in the operational position, tension in the tension bolt received in the first and second recesses acts to press the first and second contact faces together, thereby forming a tension joint that resists pivoting of the modular edge relative to the main structure.

2. A wing assembly according to claim 1 , wherein the main structure comprises at least one wing rib, and the first contact face is located on the wing rib.

3. A wing assembly according to claim 2 , wherein the first recess is formed in the wing rib.

4. A wing assembly according to claim 2 , wherein the main structure comprises a barrel nut mounted on the at least one wing rib, the first recess being formed in the barrel nut.

5. A wing assembly according to claim 1 , wherein the modular edge comprises at least one edge rib and the second recess is formed in, and the second contact face is located on, the edge rib.

6. A wing assembly according to claim 1 , wherein the modular edge comprises at least one edge rib and a spigot mounted on the edge rib and the second contact face is located on, and the second recess is formed in, the spigot.

7. A wing assembly according to claim 6 , wherein the spigot is mounted on the edge rib.

8. A wing assembly according to claim 1 , wherein the modular edge is pivotally mounted on the main structure by a fastener.

9. A wing assembly according to claim 1 , wherein the main structure comprises a plurality of wing ribs, and is configured such that, in use, a tension joint is formed between the modular edge and each wing rib, each tension joint comprising a first recess and a first contact face forming part of the main structure, a second recess and a second contact face forming part of the modular edge and a tension bolt, each tension bolt being received in a corresponding pair of first and second recesses.

10. An aircraft comprising the wing assembly of claim 1 .

11. A method of assembling a wing assembly, the wing assembly comprising:
a main structure comprising a first recess and a first contact face,
a modular edge configured to form part of the leading or trailing edge of the wing assembly, the modular edge comprising a second recess and a second contact face, wherein the modular edge is aligned with the main structure to form at least part of the leading edge or trailing edge of the wing when the modular edge is in the operational position, and
a tension bolt,
the method comprising the steps of:
mounting the modular edge to the main structure in an installation position using one more fasteners, in which the first and second contact faces are spaced apart; and then
rotating the modular edge from the installation position to an operational position solely in a circular arc about the one or more fasteners, in which the first contact face and the second contact face are abutting; and then
inserting the tension bolt into the first and second recesses; and then
tensioning the bolt to press the first and second contact faces together thereby forming a tension joint that resists rotation of the modular edge away from the operational position.

12. A method according to claim 11 , wherein the step of rotating the modular edge to an operational position comprises rotating the modular edge through an angle of at least 45 degrees.

13. A method according to claim 11 , wherein the step of tensioning the bolt comprises tightening the bolt until a predetermined torque loading is reached.

14. A wing assembly forming at least part of a wing of an aircraft, wherein
the wing assembly comprises a wing body having a first surface and a modular edge having a second surface, the modular edge being configured to form at least part of one of a leading edge of the wing assembly and a trailing edge of the wing assembly, the modular edge being clamped against the wing body by at least one releasable fixing held in tension, causing the first and second surfaces to be held together in abutting relation, and
the wing assembly modular edge is mounted on the wing body configured solely for rotation away from the wing body, when the fixing is released, to a position in which the modular edge remains connected to the wing body but with first and second surfaces being held in spaced apart relation.

Assignees

• Airbus Operations Ltd

Inventors

• Bishop Benjamin

Classifications

• B64C3/18 Primary

  Spars; Ribs; Stringers · CPC title

• B64C3/28 Primary

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

• B64C3/26

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

• B64C3/187

  Ribs · CPC title

• B64C1/26

  Attaching the wing or tail units or stabilising surfaces · CPC title