Aircraft cabin panel with core recesses for acoustic absorption

1. An aircraft cabin panel for acoustic absorption in an interior space, the aircraft cabin panel comprising:

a core layer;

a first cover layer;

a second cover layer; and

a plurality of absorbers;

wherein the first cover layer comprises a space-enclosing first surface;

wherein the second cover layer is arranged opposite the first cover layer;

wherein the first cover layer is configured be acoustically transparent;

wherein the core layer comprises a honeycomb core with a plurality of tubular or honeycomb-like cells that are open throughout the thickness of the honeycomb core;

wherein the honeycomb core on the face pointing towards the first cover layer extends parallel to the first cover layer so as to be continuously throughout, and on the face pointing towards the second cover layer comprises a plurality of recesses which extend over one or more of the plurality of cells; and

wherein each of said absorbers is accommodated in one of the recesses.

2. The panel of claim 1 , wherein the first cover layer is of a multilayer design and comprises a first lattice prepreg and a covering that forms the first surface, wherein the first lattice prepreg is laminary connected to the honeycomb core.

3. The panel of claim 2 , wherein the covering comprises a woven fabric as a surface material.

4. The panel of claim 2 , wherein the covering is of a multilayer design.

5. The panel of claim 4 , wherein a nonwoven formed fabric is provided between the surface material and the first lattice prepreg.

6. The panel of claim 1 , wherein the flow resistance of the first cover layer does not exceed 1000 Ns/m3.

7. The panel of claim 1 , wherein the weight of unit volume of the absorbers is at most as heavy as the weight of unit volume of the honeycomb core.

8. The panel of claim 1 , wherein the absorbers comprise glass wool that is contained in a wrapping or envelope.

9. The panel of claim 1 , wherein the absorbers comprise a foam.

10. The panel of claim 1 , wherein the second cover layer is impermeable to water.

11. The panel of claim 1 , wherein the second cover layer is acoustically closed.

12. The panel of claim 1 , wherein the second cover layer is of a multilayer design and comprises a second lattice prepreg.

13. The panel of claim 1 , wherein, at the edges of the panel, the honeycomb core extends across the thickness of the core layer.

14. An aircraft comprising:

a fuselage structure; and

a cabin located within the fuselage, wherein the cabin is at least in part enclosed by an interior lining comprising a plurality of panels, the panels comprising

a core layer;

a first cover layer;

a second cover layer; and

a plurality of absorbers;

wherein the first cover layer comprises a space-enclosing first surface;

wherein the second cover layer is arranged opposite the first cover layer;

wherein the first cover layer is configured to be acoustically transparent;

wherein the core layer comprises a honeycomb core with a plurality of tubular or honeycomb-like cells that are open throughout the thickness of the honeycomb core;

wherein the honeycomb core on the face pointing towards the first cover layer extends parallel to the first cover layer so as to be continuously throughout, and on the face pointing towards the second cover layer comprises a plurality of recesses which extend over one or more of the plurality of cells; and

wherein each of said absorbers are accommodated in one of the recesses.