Method for producing an aircraft fuselage and aircraft fuselage

Patent metadata

Field	Value
Publication number	US-9359090-B2
Application number	US-201013320278-A
Country	US
Kind code	B2
Filing date	May 10, 2010
Priority date	May 12, 2009
Publication date	Jun 7, 2016
Grant date	Jun 7, 2016

Abstract

Disclosed is a method for the manufacture of an aircraft fuselage with at least two fuselage barrels wherein connecting segments are firstly prepared for the formation of a transverse joint region for a later transverse joint, and the fuselage barrels are then constructed around the connecting segments; also disclosed is an aircraft fuselage with ring-type connecting segments for the formation of such a transverse joint.

First claim

What is claimed is:

1. A method of manufacturing an aircraft fuselage with at least two fuselage barrels, the method comprising:
aligning and preparing transverse joint elements with one another before joining the at least two fuselage barrels by a provisional formation of a transverse joint by:
preparing two ring-type connecting segments with identical diameters, which reproduce a fuselage cross-section in a transverse joint region;
connecting and aligning the two ring-type connecting segments with one another;
introducing seatings into the two ring-type connecting segments for accommodating connecting elements;
separating the two ring-type connecting segments;

manufacturing the at least two fuselage barrels by arranging skin fields on the two ring-type connecting segments; and
connecting the fuselage barrels by inserting the transverse joint elements into the at least two fuselage barrels, such that the at least two fuselage barrels are connected with one another in the transverse joint region by the transverse joint elements including the two ring-type connecting segments and by bringing together the two ring-type connecting segments and by inserting the connecting elements.

2. The method in accordance with claim 1 , further comprising accommodating the connecting elements in holes, which pass through radial surfaces of the two ring-type connecting segments.

3. The method in accordance with claim 2 , wherein the radial surfaces in each case close flush with a ring surface of the fuselage barrels.

4. The method in accordance with claim 3 , further comprising arranging at least two different sealing elements in an axial gap between the radial surfaces.

5. The method in accordance with claim 1 , further comprising arranging the connecting elements adjacent to one another in a single row.

6. The method in accordance with claim 5 , wherein the connecting elements are arranged in a vicinity of stringers.

7. The method in accordance with claim 5 , wherein the connecting elements are tension bolts.

8. The method in accordance with claim 1 , wherein in an assembled state, the two ring-type connecting segments form a frame.

Assignees

• Gorr Eugen
• Bense Rolf
• Airbus Operations Gmbh

Inventors

• Gorr Eugen
• Bense Rolf

Classifications

• B64F5/0009 Primary

  Operations & Transport · mapped topic

• Y10T29/49622

  Vehicular structural member making · CPC title

• B64C1/069

  Joining arrangements therefor · CPC title

• B64C1/061

  Frames · CPC title

• B64C2001/0081

  from metallic materials · CPC title