Method for producing a sandwich panel with an integrated reinforcing structure

Patent metadata

Field	Value
Publication number	US-9636901-B2
Application number	US-201414262428-A
Country	US
Kind code	B2
Filing date	Apr 25, 2014
Priority date	Sep 3, 2008
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

A Sandwich panel with a core structure, in particular with a honeycomb-shaped core structure, and plane-parallel cover layers applied to both sides of this core structure, to form a floor surface in a fuselage airframe of an aircraft, the core structure having at least one recess into which at least one reinforcing structure is integrated, wherein the at least one reinforcing structure is formed with at least one core, said core having at least one recess into which a stopper is introduced, into which at least one attachment element can be introduced to attach at least one further component to the sandwich panel, and a plurality of prepreg strips which each have a uniform fiber running direction being wound around the core. In addition, the invention relates to a method for the production of a sandwich panel according to the invention.

First claim

The invention claimed is:

1. A method for producing a sandwich panel with a core structure, the method comprising:
introducing at least one recess into the core structure;
introducing at least one recess into at least one core;
inserting a stopper into the at least one recess in the at least one core;
winding strips comprising a fiber-reinforced prepreg material around the core to form at least one reinforcing structure, wherein the strips have a uniform fiber running direction and are guided around outer edges of the core to surround the core on all sides;
introducing the at least one reinforcing structure, at least in certain regions, in an interlocking manner into the at least one recess in the core structure while creating a material bond;
applying cover layers to both sides of the core structure, thereby forming a sandwich panel;
curing the at least one reinforcing structure and the cover layers by applying pressure and/or temperature; and
introducing a hole into the stopper after curing the at least one reinforcing structure and the cover layers so an attachment element can be introduced into the hole to attach a further component to the sandwich panel.

2. The method according to claim 1 , wherein at least certain regions of the at least one reinforcing structure are adhesively bonded with the at least one recess in the core structure.

3. The method according to claim 1 , wherein a cover layer is joined to the core structure of the sandwich panel before the at least one reinforcing structure is introduced.

4. The method according to claim 1 , wherein the core structure comprises a honeycomb-shaped core structure which is provided on both sides with substantially parallel cover layers.

Assignees

• Airbus Operations Gmbh

Inventors

• Jürgens Manuela (Richter)

Classifications

• Y10T428/24157

  Filled honeycomb cells [e.g., solid substance in cavities, etc.] · CPC title

• B32B3/14

  characterised by a face layer formed of separate pieces of material {which are juxtaposed side-by-side (B32B5/02 takes precedence)} · CPC title

• B29D99/0021

  provided with plain or filled structures, e.g. cores, placed between two or more plates or sheets, e.g. in a matrix · CPC title

• B32B5/18

  characterised by features of a layer {of} foamed material · CPC title

• B32B5/26

  another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)} · CPC title