Sandwich structure

Patent metadata

Field	Value
Publication number	US-10450052-B2
Application number	US-201615216984-A
Country	US
Kind code	B2
Filing date	Jul 22, 2016
Priority date	Jul 22, 2015
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

A sandwich structure with an outer cover layer, inner cover layer, core layer, and pins extending through the core layer. The sandwich structure has a large core thickness resistant to crack formation and to detachment of the cover layers from the core layer. An anchor layer is between the outer and inner cover layers and divides the core layer, at least in areas, into an outer core layer section and inner core layer section. An outer group of pins extends through the outer core layer section and an inner group of pins extends through the inner core layer section. The outer group pins are connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the inner group pins are connected to the anchor layer with their first end and to the inner cover layer with their opposite second end.

First claim

The invention claimed is:

1. A sandwich structure comprising:
an outer cover layer;
an inner cover layer disposed opposite the outer cover layer in a thickness direction;
a core layer, which, as viewed in the thickness direction, is disposed between the outer and the inner cover layers and connects them; and
a plurality of pins including at least an outer group of pins and an inner group of pins, which extend between the outer and the inner cover layers, through the core layer;
an anchor layer between the outer and the inner cover layers, the anchor layer extending transversely to the thickness direction and dividing the core layer, at least in areas, into an outer core layer section in abutment with the outer cover layer and an inner core layer section in abutment with the inner cover layer;
the outer group of pins extending through the outer core layer section and the inner group of pins extending through the inner core layer section; and
the pins of the outer group being connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the pins of the inner group being connected to the anchor layer with their first end and to the inner cover layer with their opposite second end,
wherein the anchor layer comprises an outer anchor layer part pointing to the outer cover layer and an inner anchor layer part pointing to the inner cover layer,
wherein the outer and inner anchor layer parts run transversely to the thickness direction,
wherein between the outer and inner anchor layer parts, the core layer has a middle core layer section through which a middle group of pins extends,
wherein the outer group of pins are connected to the outer anchor layer part with their first end and to the outer cover layer with their opposite second end,
wherein the inner group of pins are connected to the inner anchor layer section with their first end and to the inner cover layer with their opposite second end, and
wherein the middle group of pins are connected to the outer anchor layer part with their first end and to the inner anchor layer part with their opposite second end.

2. The sandwich structure according to claim 1 , wherein the outer and the inner cover layers, the anchor layer, and the pins are formed monolithically by co-curing with each other from a fiber composite material.

3. The sandwich structure according to claim 1 , wherein at a layer border, the anchor layer is cured monolithically together with the outer and/or the inner cover layer(s).

4. The sandwich structure according to claim 3 , wherein the sandwich structure has a peripheral area at which the cover layers are cured monolithically with one another, wherein at the peripheral area of the sandwich structure, the anchor layer is joined with its layer border to the outer and inner cover layers.

5. An aircraft comprising a fuselage and a wing,
wherein the wing extends between a wing tip pointing away from the fuselage and a wing root opposite the wing tip, with which wing root the wing is fastened to the fuselage,
wherein the wing is formed as a shell structure with an upper shell part and a lower shell part, and
wherein the upper shell part and/or the lower shell part comprise a sandwich structure in an area of the wing root, the sandwich structure comprising:
an outer cover layer;
an inner cover layer disposed opposite the outer cover layer in a thickness direction;
a core layer, which, as viewed in the thickness direction, is disposed between the outer and the inner cover layers and connects them; and
a plurality of pins including at least an outer group of pins and an inner group of pins, which extend between the outer and the inner cover layers, through the core layer;
an anchor layer between the outer and the inner cover layers, the anchor layer extending transversely to the thickness direction and dividing the core layer, at least in areas, into an outer core layer section in abutment with the outer cover layer and an inner core layer section in abutment with the inner cover layer;
the outer group of pins extending through the outer core layer section and the inner group of pins extending through the inner core layer section; and
the pins of the outer group being connected to the anchor layer with their first end and to the outer cover layer with their opposite second end, and the pins of the inner group being connected to the anchor layer with their first end and to the inner cover layer with their opposite second end,
wherein spacing between the outer and inner cover layers decreases from the wing root towards the wing tip, and wherein starting from the wing root, the anchor layer extends towards the wing tip at least as far as a location at which the spacing between the outer and inner cover layers is between 30 mm and 200 mm.

Assignees

• Airbus Operations Gmbh

Inventors

• Joern Paul
• Grase Karim

Classifications

• B64C3/20 Primary

  Integral or sandwich constructions · CPC title

• B64C1/10

  Bulkheads · CPC title

• B29C70/24

  oriented in at least three directions forming a three-dimensional [3D] structure · 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