Sandwich panel for sound absorption
View Patent ↗An aircraft cabin panel for sound absorption, with a sandwich construction, comprising a core layer that comprises a plurality of tube-like or honeycomb-like cells that extend in an open manner across the thickness of the core layer and that are separated from each other by cell walls and that are uniform in design. A first cover layer faces away from the sound field, as well as a second cover layer that faces towards the sound field and that comprises a plurality of perforation holes and adjacent cells are interconnected by way of apertures in the cell walls. The perforation of the second cover layer comprises a distance (b) between holes, which distance exceeds the opening width (c) of the cells of the core layer, wherein the first cover layer is closed and wherein the cell walls comprise a perforation so that they are acoustically transparent in the direction parallel to the cover layers.
1. An aircraft cabin panel for sound absorption having a sandwich-like construction comprising:
a core layer comprising a plurality of tube-like or honeycomb-like cells that extend in an open manner across the thickness of the core layer and that are separated from each other by cell walls and that are uniform in design;
a first cover layer that faces away from a sound field; and
a second cover layer that faces towards the sound field and comprises a plurality of perforation holes;
wherein adjacent cells are interconnected by way of apertures in the cell walls wherein the perforation holes of the second cover layer have a distance (b) between holes, which distance exceeds an opening width (c) of the cells of the core layer;
wherein the first cover layer is closed; and
wherein the cell walls comprise a perforation so that they are acoustically transparent in the direction parallel to the cover layers.
2. The aircraft cabin panel of claim 1 , wherein the diameter of the holes of the second cover layer is less than 1 mm, and the percentile of perforated surface is less than 1%.
3. The aircraft cabin panel of claim 1 , wherein the second cover layer is multi-layered, comprising a layer that determines the strength, and a layer of one of a perforated film or foil.
4. The aircraft cabin panel of claim 1 , wherein at least some of the hollow spaces of the core layer are filled with a porous sound-absorbent material.
5. The aircraft cabin panel of claim 1 , wherein the hollow spaces of the core layer differ in height.
6. The aircraft cabin panel of claim 1 , wherein further layers are provided between the first cover layer and the second cover layer.
7. The aircraft cabin panel of claim 1 , wherein the cover layers comprise fiber reinforced materials.
8. A device for sound absorption in an aircraft cabin in which between an aircraft supporting structure and the cabin space an interior lining arrangement formed by panels is provided, wherein at least one or more of the panels are sound-absorbent aircraft cabin panels comprising:
a core layer comprising a plurality of tube-like or honeycomb-like cells that extend in an open manner across the thickness of the core layer and that are separated from each other by cell walls and that are uniform in design;
a first cover layer that faces away from a sound field; and
a second cover layer that faces towards the sound field and comprises a plurality of perforation holes;
wherein adjacent cells are interconnected by way of apertures in the cell walls wherein the perforation holes of the second cover layer have a distance (b) between holes, which distance exceeds an opening width (c) of the cells of the core layer;
wherein the first cover layer is closed; and
wherein the cell walls comprise a perforation so that they are acoustically transparent in the direction parallel to the cover layers.