DEVICE, IN PARTICULAR CONNECTION ROD, FOR BRACING A FUSELAGE STRUCTURE OF AN AIRCRAFT AND/OR FOR FASTENING A COMPONENT

• US 20110108668A1
• Filed: 01/11/2008
• Published: 05/12/2011
• Est. Priority Date: 01/22/2007
• Status: Active Grant

• Current Assignee: Airbus Operations GmbH (Airbus SE)
• Original Assignee: Airbus Deutschland GmbH (Airbus SE)
• Inventors: Benthien, Hermann
• Granted Patent: US 8,382,038 B2
• Time in Patent Office: Days
• 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 fibres 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. Device (18,61), in particular a connection rod (1,19), for bracing a fuselage structure (9,10,27,28,45,74) of an aircraft and/or for fastening a component (65) on the fuselage structure (9,10,27,28,45,74), comprising a central portion (2,20,62) and two end portions (3,4,21,22,63,64) which adjoin this, characterised in that a joint (29,30,53,70) is arranged in the region of at least one end portion (3,4,21,22,63,64), the joint (29,30,53,70) being integrated in the fuselage structure (9,10,27,28,45,74) or in the component (65) and being pivotable around at least one rotational axis (35,36).

2. Device (18) according to Patent claim 1, characterised in that a threaded rod (23,24,54) is respectively screwed onto the end portions (3,4,21,22).

3. Device (18) according to Patent claim 1 or 2, characterised in that the at least one joint (29,30,53) is formed with a barrel nut (31,32,47) which is rotatably received in a bearing bore (33,34) in the fuselage structure (9,10,27,28,45) and into which a threaded rod (23,24,54) can be screwed.

4. Device (18) according to one of Patent claims 1 to 3, characterised in that a passage bore (41,42) is arranged in the fuselage structure (9,10,27,28,45), the diameter of the passage bore (41,42) being larger than a diameter of the threaded rods (23,24,54) in order to enable the screwing of one of the threaded rods (23,24,54) into the joint (29,30,53) and thus a sufficient mobility.

5. Device (18) according to one of Patent claims 1 to 4, characterised in that the fuselage structure (9,10,27,28,45) has a thickening (39,40,50) in the region of the bearing bore (33,34).

6. Device (18) according to one of Patent claims 1 to 5, characterised in that an inner barrel nut (51) is pivotably received in the barrel nut (31,32,47), wherein the threaded rod (23,24,54) can be screwed into the inner barrel nut (51) and the threaded rod (23,24,54) can be pivoted around two rotational axes (56,57).

7. Device (18) according to one of Patent claims 1 to 6, characterised in that the rotational axes (56,57) of the barrel nuts (31,32,47) and of the inner barrel nut (51) enclose an angle of 90°

to one another.

8. Device (18) according to one of Patent claims 1 to 7, characterised in that the barrel nut (47) has a circumferential flange (48) and a circumferential groove with a retaining ring (49) in order to prevent an axial displacement in the bearing bore (46).

9. Device (18) according to one of Patent claims 1 to 8, characterised in that the central portion (2,20) of the connection rod (1,19) respectively tapers towards the end portions (3,4,21,22).

10. Device (18) according to one of Patent claims 1 to 9, characterised in that the barrel nuts (31,32,47,51) are provided with a friction-reducing layer and/or are formed with a material with a low coefficient of friction.

11. Device (61) according to Patent claim 1, characterised in that the end portions (63,64) adjoining the central portion (62) on both sides respectively have a thread at least in sections.

12. Device (61) according to Patent claim 11, characterised in that the device (61) has a joint (70) formed with a barrel nut (67), wherein the barrel nut (67) is rotatably received in a bearing bore (66) in the component (65) and an end portion (63) is screwed into the barrel nut (67) and the other end portion (64) is screwed to the fuselage structure (74).

13. Device (61) according to Patent claim 11 or 12, characterised in that a passage bore (71) is arranged in the component (65), the diameter of the passage bore (71) being larger than a diameter of the end portion (63) in order to enable a sufficient mobility.

14. Device (61) according to one of Patent claims 11 to 13, characterised in that the component (65) has a thickening (68) in the region of the bearing bore (66).

15. Device (61) according to one of Patent claims 10 to 14, characterised in that an inner barrel nut (69) is pivotably received in the barrel nut (67), wherein the end portion (63) can be screwed into the inner barrel nut (69).

16. Device (61) according to one of Patent claims 10 to 15, characterised in that the component (65) is in particular a vertical support of a lining frame for mounting a plurality of seats.