Fastening device

Patent metadata

Field	Value
Publication number	US-10731683-B2
Application number	US-201615166464-A
Country	US
Kind code	B2
Filing date	May 27, 2016
Priority date	May 29, 2015
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

The invention relates to an aircraft structure, the aircraft structure comprising a first component and a second component. A fastening device fastens the first component to the second component, wherein the fastening device comprises a clamping member, and a fastening member. The fastening member has a longitudinal axis, and the clamping member is associated with the first component such that the clamping member is movable in a first direction and is fixed in position in a second direction, the first direction being parallel to the longitudinal axis of the fastener, wherein the fastener extends through the second component into engagement with the clamping member and holds the clamping member against the second component. The fastening device may hold the first component and second component in a fixed position relative to one another, in at least one direction, without applying a clamping force between the first component and second component.

First claim

The invention claimed is:

1. An aircraft structure comprising:
a first component having a central aperture extending between opposing faces thereof, and a clamping member receiving portion, surrounding the central aperture, recessed within one of the faces;
a second component having an aperture extending between opposing faces thereof;
a clamping member for fastening the first component to the second component, the clamping member having a main body having an aperture extending between opposing faces thereof and at least one connecting portion that extends away from one of the faces of the main body, wherein the main body is positionable within the clamping member receiving portion between the first component and the second component, such that the first component and the second component can contact each other and the at least one connecting portion extends through a respective aperture formed through the first component;
a fastener with a longitudinal axis; and
an anchor nut arranged on an opposite side of the first component from the main body of the clamping member, wherein the clamping member is engagable with the anchor nut via the at least one connecting portion being in contact with a surface of the anchor nut that faces towards the main body of the clamping member,
wherein the fastener is configured to extend through the apertures in the second component and the clamping member and the central aperture in the first component, and threadedly engage the anchor nut,
wherein the clamping member is movable, relative to the first component, in a first direction parallel to the longitudinal axis of the fastener and is restricted from movement in a second direction, and
wherein, when the clamping member fastens the first and second components, the clamping member and anchor nut are slidable relative to the first component via threaded engagement of the fastener with the anchor nut, such that the main body of the clamping member is slidable from a first position within the clamp receiving portion to a second position which at least partially extends from the clamp receiving portion and is against the second component.

2. The aircraft structure according to claim 1 , wherein the at least one connecting portion is at least two connecting portions, and wherein the clamping member is secured to the anchor nut by the at least two connecting portions that are spaced with respect to each other.

3. The aircraft structure according to claim 2 , wherein the at least two connecting portions are associated with distinct apertures formed through the first component, the apertures being located such that rotational movement of the clamping member relative to the first component, or movement of the clamping member in the plane of the first component, is prevented.

4. The aircraft structure according to claim 2 , wherein the at least two connecting portions define a gap between the anchor nut and the main body of the clamping member.

5. The aircraft structure according to claim 1 , wherein the anchor nut comprises a threaded aperture.

6. The aircraft structure according to claim 1 , wherein the fastener is a threaded bolt.

7. The aircraft structure according to claim 1 , wherein the second component comprises a countersunk aperture for receiving a countersunk bolt end of the fastener.

8. The aircraft structure according to claim 1 , wherein the first component is a metal component.

9. The aircraft structure according to claim 1 , wherein the second component is a composite component.

10. The aircraft structure according to claim 1 , comprising a plurality of clamping members that are each movable in a different direction to others of the plurality of clamping members and fixed in a different direction to the others of the plurality of clamping members.

11. An aircraft comprising at least one aircraft structure according to claim 1 .

12. A method of joining a first component and a second component, the method comprising:
providing a first component having a central aperture extending between opposing faces thereof, and a clamping member receiving portion, surrounding the central aperture, recessed within one of the faces;
providing a second component having an aperture extending between opposing faces thereof;
providing a clamping member, which has a main body having an aperture extending between opposing faces thereof and least one connecting portion that extends away from one of the faces of the main body;
locating the clamping member at least partially within the clamping member receiving portion so that the main body is between the first component and the second component and the at least one connecting portion extends through a respective aperture formed through the first component;
arranging an anchor nut on an opposite side of the first component from the main body of the clamping member, so that the at least one connecting portion is in contact with a surface of the anchor nut that faces towards the main body of the clamping member;
attaching, via the at least one connecting portion, the anchor nut to the clamping member, such that the clamping member is movable, relative to the first component, in a first direction that is in a direction of extension of the at least one connecting portion and restricted from movement in a second direction; and
inserting a fastener through the apertures in the second component and the clamping member and the central aperture in the first component, and threadedly engaging the fastener with the anchor nut,
wherein, when the clamping member fastens the first and second components, the clamping member and anchor nut are slidable relative to the first component via threaded engagement of the fastener with the anchor nut, such that the main body of the clamping member is slidable from a first position within the clamp receiving portion to a second position which at least partially extend from the clamp receiving portion and is against the second component.

Assignees

• Airbus Operations Ltd

Inventors

• Christensen Richard
• Agadi Harish
• Randle Lee

Classifications

• B64C7/00 Primary

  Structures or fairings not otherwise provided for · CPC title

• F16B5/0233

  allowing for adjustment perpendicular to the plane of the plates · CPC title

• F16B5/025

  specially designed to compensate for misalignement or to eliminate unwanted play · CPC title

• F16B5/0056

  by moving the sheets, plates or panels or the interlocking key perpendicular to the main plane · CPC title

• F16B2/065 Primary

  using screw-thread elements (F16B2/08 - F16B2/12 take precedence) · CPC title