Device and method for assembling two sections of aircraft fuselage

Patent metadata

Field	Value
Publication number	US-10150553-B2
Application number	US-201213533266-A
Country	US
Kind code	B2
Filing date	Jun 26, 2012
Priority date	Jun 27, 2011
Publication date	Dec 11, 2018
Grant date	Dec 11, 2018

Abstract

A device and method for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.

First claim

The invention claimed is:

1. An assembly, comprising:
two aircraft fuselage sections assembled end to end longitudinally and each of which comprises a skin as well as omega-shaped longitudinal stiffeners directly attached to said skin and distributed around a longitudinal axis of said section, said longitudinal stiffeners being arranged so that each longitudinal stiffener of one of the sections is substantially aligned with a corresponding longitudinal stiffener of the other section; and
at least one assembly device comprising two fishplate elements for fishplating two longitudinal stiffeners and at least one demountable connecting member,
wherein each of said fishplate elements comprises a longitudinal sole plate, a web, and a transverse support head, the two fishplate elements being separated from each other in a longitudinal direction by a circumferential frame,
wherein each of the two longitudinal stiffeners include a sole plate and a web,
wherein the respective transverse support heads of the two fishplate elements are clamped to each other by the demountable connecting member so as to allow a transmission of longitudinal tension and compression forces between the two fishplate elements,
wherein the respective longitudinal sole plates of the two fishplate elements are directly attached respectively to respective sole plates of two corresponding longitudinal stiffeners substantially aligned with each other and respectively forming part of said fuselage sections, and
wherein the respective webs of the two fishplate elements are directly attached respectively to respective webs of the two corresponding longitudinal stiffeners.

2. The assembly according to claim 1 , wherein at least one element of the circumferential frame is interposed between the respective transverse support heads of the two fishplate elements.

3. The assembly according to claim 2 , in which said element of the circumferential frame comprises a foot interposed between at least a part of each sole plate of at least one of the two fishplate elements and the skin of the corresponding fuselage section.

4. The assembly according to claim 1 , also comprising a circumferential splice directly attached to said respective skins of said fuselage sections, and to which a part of each sole plate of each of the two fishplate elements is fixed directly attached.

5. The assembly according to claim 1 , wherein each of the two fishplate elements comprises a single sole plate that covers two respective contiguous sole plates of two circumferentially consecutive longitudinal stiffeners of the corresponding fuselage section.

6. The assembly according to claim 1 , wherein
each of said longitudinal stiffeners comprises two sole plates separated circumferentially from each other and mutually connected by a body of the longitudinal stiffener, and
each of the two fishplate elements comprises two sole plates that are respectively directly attached to said two sole plates of a corresponding longitudinal stiffener and which are connected to each other by said transverse support head of the fishplate element.

7. An aircraft fuselage, comprising at least one assembly according to claim 1 .

8. An aircraft comprising a fuselage according to claim 7 .

9. The assembly according to claim 1 , wherein the respective transverse support heads are directly attached to opposite sides of the circumferential frame by the demountable connecting member.

10. The assembly according to claim 6 , wherein the demountable connecting member is a bolt and nut, the bolt passing through orifices in the respective transverse support heads and in the circumferential frame.

11. The assembly according to claim 1 , wherein each of the two fishplate elements terminate at the respective transverse support heads.

12. The assembly according to claim 1 , wherein each of the two fishplate elements includes a recess to receive a foot of the circumferential frame.

13. A method of assembling two aircraft fuselage sections, each of which comprises a skin and longitudinal stiffeners directly attached to said skin and distributed around a longitudinal axis of said fuselage section, with at least one assembly device for assembling the two aircraft fuselage sections, said device comprising two fishplate elements for fishplating two longitudinal stiffeners substantially aligned with respect to each other and belonging respectively to said fuselage sections, wherein each of the two fishplate elements comprises at least one longitudinal sole plate to be directly attached to a corresponding longitudinal stiffener, and a transverse support head, the two fishplate elements being separated from each other in a longitudinal direction by a circumferential frame, said assembly device also comprising at least one demountable connecting member to mutually clamp the respective support heads of the two fishplate elements to allow a transmission of longitudinal forces between the two fishplate elements, said method comprising at least steps of:
end-to-end positioning, in the longitudinal direction, of the respective skins of said fuselage sections;
directly attaching a sole plate of one of the two fishplate elements to a sole plate of a corresponding longitudinal stiffener of a first one of said fuselage sections;
directly attaching a sole plate of the other of the two fishplate elements to a sole plate of a corresponding longitudinal stiffener of the second of said fuselage sections; and
subsequently to the above three steps, mutual clamping of the respective transverse support heads of the two fishplate elements by means of the at least one demountable connecting member so as to allow longitudinal tension and compression forces to be transmitted between the two fishplate elements.

14. A method according to claim 13 , wherein said step of directly attaching the sole plate of the one of the two fishplate elements is implemented before said step of end-to-end positioning of the skins of the fuselage sections.

15. A method according to claim 14 , also comprising a step of temporary fixing of the sole plate of the other of the two fishplate elements on the sole plate of said corresponding longitudinal stiffener of the second of said fuselage sections, implemented before said step of end-to-end positioning of the skins of the fuselage sections.

16. A method according to claim 15 , also comprising a step of a directly attaching the sole plate of the other of the two fishplate elements on the sole plate of said corresponding longitudinal stiffener of the second of said fuselage sections, after the mutual clamping of the respective transverse support heads of the two fish plate elements.

Assignees

• Cacciaguerra Bruno
• Depeige Alain
• Lacombe Jean Claude
• Cazeneuve Helene
• Castanet Marc Antoine
• Airbus Operations Sas

Inventors

• Cacciaguerra Bruno
• Depeige Alain
• Lacombe Jean-Claude
• Cazeneuve Hélène
• Castanet Marc-Antoine

Classifications

• Y10T29/49622

  Vehicular structural member making · CPC title

• B64C2001/0081

  from metallic materials · CPC title

• B64F5/10

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title

• B64C1/069 Primary

  Joining arrangements therefor · CPC title

• B64C1/068

  Fuselage sections · CPC title