Device, in particular connection rod, for bracing a fuselage structure of an aircraft and/or for fastening a component

• US 8,382,038 B2
• Filed: 01/11/2008
• Issued: 02/26/2013
• Est. Priority Date: 01/22/2007
• Status: Expired due to Fees

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Operations GmbH (Airbus SE)
• Inventors: Benthien, Hermann
• Primary Examiner(s): Ellis, Christopher P
• Assistant Examiner(s): Badawi, Medhat
• Application Number:
  US12/521,247
• Publication Number:
  US 20110108668A1
• Time in Patent Office: 1,873 Days
• Field of Search: 244/131, 244/119, 244/117, 244/118.5, 244/118.6, 244/129.5, 244/129.4
• US Class Current: 244/131
• CPC Class Codes: B60P 7/0807 Attachment points
• CPC Class Codes: B64D 9/00 Equipment for handling freight; Equipment for facilitating passenger embarkation or the like emergency equipment B64D17/00, B64D19/00, B64D25/00; structures integral with fuselage to facilitate loading, fuselage floors specially adapted for freight, steps mounted on and retractable within aircraft B64C; ground installations B64F
• CPC Class Codes: B64D 9/003 Devices for retaining pallets or freight containers securing freight containers on vehicles B60P7/00
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

The invention relates to a device, in particular a connection rod, for bracing a fuselage structure and/or for fastening components on the fuselage structure.

In one embodiment, the joints are integrated into fuselage structure for linking on both sides of connection rod to fuselage structure. As a result of the integration of joints, a reduced number of individual parts is produced in comparison to previously known embodiments, which leads to a reduction in weight, a reduced maintenance and servicing outlay and an improved reliability against failure. Moreover, device according to the invention enables the introduction of forces in the region of neutral fibers of fuselage structure. A further configuration of device provides only a one-sided articulated linking of a component to fuselage structure by means of (first) end portion. Second end portion is screwed to fuselage structure. To this end, both end portions are provided with a thread at least in sections.

Claims

1. A device comprising a connection rod combined with a fuselage structure of an aircraft for bracing the fuselage structure of an aircraft and for fastening a component on the fuselage structure, said device comprising a central portion and two end portions, wherein a joint is arranged in the region of at least one end portion, the joint being integrated in the fuselage structure or in the component and being pivotable around at least one rotational axis, characterized in that the device has said joint is formed with a barrel nut, wherein the barrel nut is rotatably received in a bearing bore in the component and an end portion is screwed into the barrel nut and the other end portion is screwed to the fuselage structure and that the component is comprised of a vertical support of a lining frame for mounting a plurality of seats;

and wherein an inner barrel nut is pivotably received in the barrel nut, wherein the end portion is screwed into the inner barrel nut (−

69).

2. The device according to claim 1, wherein a threaded rod is respectively screwed onto the end portions.

3. The device according to claim 1, wherein the at least one joint is formed with a barrel nut which is rotatably received in a bearing bore in the fuselage structure and into which a threaded rod (23, 24, 54) can be screwed.

4. The device according to claim 2, wherein a passage bore is arranged in the fuselage structure, the diameter of the passage bore being larger than a diameter of the threaded rods in order to enable the screwing of one of the threaded rods into the joint and thus a sufficient mobility.

5. The device according to claim 1, wherein the fuselage structure has a thickening in the region of the bearing bore.

6. The device according to claim 3, wherein, wherein the threaded rod can be screwed into the inner barrel nut and the threaded rod can be pivoted around two rotational axes.

7. The device according to claim 6, wherein the rotational axes of the barrel nuts and of the inner barrel nut enclose an angle of 90°

to one another.

8. The device according to claim 3, wherein the barrel nut has a circumferential flange and a circumferential groove with a retaining ring in order to prevent an axial displacement in the bearing bore.

9. The device according to claim 1, wherein the central portion of the connection rod respectively tapers towards the end portions.

10. The device according to claim 6, wherein the barrel nuts are provided with a friction-reducing layer and/or are formed with a material with a low coefficient of friction.

11. The device according to claim 1, wherein the end portions adjoining the central portion on both sides respectively have a thread at least in sections.

12. The device according to claim 11, wherein a passage bore is arranged in the component, the diameter of the passage bore being larger than a diameter of the end portion in order to enable a sufficient mobility.

13. The device according to claim 1, wherein the component has a thickening in the region of the bearing bore.