Shell segment of an aircraft and a production method

Patent metadata

Field	Value
Publication number	US-9637213-B2
Application number	US-201414287625-A
Country	US
Kind code	B2
Filing date	May 27, 2014
Priority date	May 28, 2013
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

A segment and a method for producing such a segment, in particular for an aircraft, having a skin field and a skin field stiffening structure. The skin field and stiffening structure are made from fiber-reinforced plastic materials. The stiffening structure is bonded to an inner surface of the skin field and comprises a multiplicity of first stiffeners and mounts which are formed integrally with the first stiffeners and extend in a transverse direction of the first stiffeners for the connection of second stiffeners to form an integral lattice structure. Reinforcement elements are provided for mechanically fixing the mounts to the skin field. Each reinforcement element has a connection section and a blocking section having an extension in a direction inclined to the connection section. The connection section penetrates the skin field and the mounts, and the blocking section is in contact with an outer surface of the skin field.

First claim

The invention claimed is:

1. A shell segment of an aircraft, comprising:
a skin field,
a stiffening structure for purposes of stiffening the skin field,
wherein the skin field and the stiffening structure are made from fiber-reinforced plastic materials, and
wherein the stiffening structure is bonded to an inner surface of the skin field and comprises a multiplicity of first stiffeners and a multiplicity of mounts which are formed integrally with the first stiffeners and which extend in the transverse of the first stiffeners for the connection of second stiffeners, and
a multiplicity of reinforcement elements for fixing the mounts mechanically to the skin field,
wherein each mount comprises two flange layers, which are bonded together on their surfaces facing each other,
wherein each reinforcement element has a connection section and only one blocking section, the blocking section having an extension in a direction inclined to the connection section,
wherein each connection section penetrates the skin field and is inserted only between the surfaces of the flange layers of one of the mounts without penetrating into the flange layers, such that said connection section is in direct contact only with the surfaces of the respective flange layers facing each other, and
wherein the blocking section is in contact with an outer surface of the skin field.

2. The shell segment according to claim 1 , wherein each reinforcement element has a pin-like shape with a shaft as a connecting section and a head as a blocking section.

3. The shell segment according to claim 2 , wherein each blocking section is positioned in a recess of the outer surface of the skin field.

4. The shell segment according to claim 1 , wherein each reinforcement element has a filament-like shape having a straight section as a connection section and an angled section as a blocking section.

5. The shell segment according to claim 4 , wherein the reinforcement elements are positioned in crossed rows.

6. The shell segment according to claim 5 , wherein the blocking sections of the crossed rows face away from each other.

7. The shell segment according to claim 1 , wherein a cover layer is attached to the outer surface of the skin field.

8. A method for building a shell segment of an aircraft, with the steps:
manufacturing an integral stiffening structure from fiber-reinforced plastic materials, with a multiplicity of first stiffeners and integral mounts extending transverse to the first stiffeners for the connection of second stiffeners, each mount comprising two flange layers, which are bonded together on their surfaces facing each other,
providing a skin field made from fiber-reinforced plastic materials,
bonding the stiffening structure to an inner surface of the skin field to stiffen the skin field, and
fixing the mounts to the skin field mechanically by reinforcement elements,
wherein each reinforcement element has a connection section and only one blocking section, the blocking section having an extension in a direction inclined to the connection section,
wherein each connection section of the reinforcement elements penetrates the skin field and is inserted only between the surfaces of the flange layers of one of the mounts without penetrating into the flange layers, such that said connection section is in direct contact only with the surfaces of the respective flange layers facing each other, and the blocking section is in contact with an outer surface of the skin field.

9. The method according to claim 8 , wherein the reinforcement elements are inserted from the outer surface of the skin field.

10. The method according to claim 8 , wherein the reinforcement elements are sewed, wherein filament loops on the outer surface of the skin field are created and are tilt against the outer surface.

Assignees

• Airbus Operations Gmbh

Inventors

• Joern Paul
• Mueller Markus

Classifications

• B29C65/72

  by combined operations {or combined techniques}, e.g. welding and stitching · CPC title

• B32B2038/0052

  Other operations not otherwise provided for · CPC title

• B29C66/7212

  characterised by the composition of the fibres · CPC title

• B29D99/0014

  provided with ridges or ribs, e.g. joined ribs · CPC title

• B32B7/08

  by mechanical means · CPC title