# US 2014/0151504 A1 · Aircraft fuselage structure and method

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- Number: US 2014/0151504 A1
- Document ID: US20140151504A1
- Status: Published application
- Kind: A1
- Application number: 14/084,692
- Filed: 2013-11-20
- Published: 2014-06-05
- Earliest claimed: 2012-11-30
- Assignees: Airbus Operations GmbH
- Applicants: Airbus Operations GmbH
- Inventors: Magdalena Boyen; Wolfgang Eilken; Wolfgang Schulze
- Web page: https://patentgrep.com/patent/US20140151504A1

## CPC

- B64C 1/068: {Fuselage sections}
- B64C 1/061: {Frames}
- B64C 1/069: {Joining arrangements therefor}
- B64F 5/10: Manufacturing or assembling aircraft, e.g. jigs therefor
- B64C 2001/0081: {from metallic materials}
- Y10T 29/49622: Vehicular structural member making
- B64C: AEROPLANES; HELICOPTERS
- B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

An aircraft fuselage structure having a first fuselage barrel section and a second fuselage section barrel which are joined by tension fasteners extending through frame holes. A shank diameter of the fasteners is smaller than a respective frame hole diameter. A first positive locking element and a second positive locking element is provided forming a form-fit area with the first positive locking element in the circumferential direction. A method for producing such an aircraft fuselage section is also provided.

## Claims

### Claim 1

An aircraft fuselage structure, comprising:
a first fuselage section having
a first skin and
a first frame half which is attached to the first skin via a first flange portion and which has a first web portion extending from the first flange portion, and
a second fuselage section having
a second skin and
a second frame half which is attached to the second skin via a second flange portion and which has a second web portion extending from the second flange portion,
wherein
the frame halves are connected by fasteners extending through frame holes in the web portions and forming a single frame,
wherein
a shank diameter of the fasteners is smaller than a respective frame hole diameter, and
wherein
the first web portion has a first positive locking element and the second web portion has a second positive locking element both establishing a form-fit area in a circumferential direction.

### Claim 2 (depends on 1)

The aircraft fuselage structure according to claim 1, wherein both the first web portion and the second web portion have at least two positive locking elements, wherein the two positive locking elements are positioned in a single plane.

### Claim 3 (depends on 1)

The aircraft fuselage structure according to claim 1, wherein each first positive locking element has a shoulder and each second positive locking element has a counter shoulder.

### Claim 4 (depends on 3)

The aircraft fuselage structure according to claim 3, wherein the two positive locking elements laying in one plane have opposite counter surfaces.

### Claim 5 (depends on 1)

The aircraft fuselage structure according to claim 1, wherein each positive locking element has a structure comprising a plurality of parallel teeth.

### Claim 6 (depends on 5)

The aircraft fuselage structure according to claim 5, wherein the teeth of each structure are spaced apart from each other in the circumferential direction.

### Claim 7 (depends on 1)

The aircraft fuselage structure according to claim 1, wherein fasteners extend through web holes in the form-fit areas.

### Claim 8 (depends on 1)

A method for producing an aircraft fuselage structure according to claim 1, comprising
attaching frame halves to the skin of two fuselage sections via flange portions,
wherein before the attachment of the frame halves to the skin or afterwards, corresponding finished frame hole patterns are introduced in the web portions of the frame halves,
positioning the fuselage sections opposite to each other,
aligning the fuselage sections in horizontal, vertical and circumferential directions, and
joining the fuselage sections by inserting fasteners through the frame holes, wherein the fasteners have a shank diameter that is smaller than a respective frame hole diameter.