# US 12,179,905 B2 · Cladding element having a heating layer in a sandwich construction

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- Number: US 12,179,905 B2
- Document ID: US12179905B2
- Status: Granted
- Kind: B2
- Application number: 16/691,821
- Filed: 2019-11-22
- Published: 2020-05-28
- Granted: 2024-12-31
- Earliest claimed: 2018-11-23
- Assignees: Airbus Operations GmbH
- Applicants: Airbus Operations GmbH
- Inventors: Rainer Müller; Andreas Baatz; Dietmar Voelkle; Florian Hesselbach; Tobias Lechner; Norbert Staudigel; Benjamin Joemann
- Web page: https://patentgrep.com/patent/US12179905B2

## CPC

- B64C 1/40: Sound or heat insulation {, e.g. using insulation blankets}
- B32B 3/04: characterised by {at least one} layer folded at the edge, e.g. over another layer {; characterised by at least one layer enveloping or enclosing a material}
- B32B 3/08: characterised by added members at particular parts {(layer formed of separate pieces of material which are juxtaposed side-by-side B32B3/14, B32B3/18)}
- B32B 3/12: characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
- B32B 3/266: {characterised by an apertured layer, the apertures going through the whole thickness of the layer, e.g. expanded metal, perforated layer, slit layer regular cells B32B3/12}
- B32B 5/06: characterised by a fibrous {or filamentary} layer {mechanically connected, e.g. by needling} to another layer, e.g. of fibres, of paper
- B32B 5/18: characterised by features of a layer {of} foamed material
- B32B 5/245: {another layer next to it being a foam layer}
- B32B 5/26: another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)}
- B32B 7/025: Electric or magnetic properties
- B32B 7/027: Thermal properties
- B32B 17/02: in the form of fibres or filaments
- B32B 27/12: next to a fibrous or filamentary layer
- B32B 27/34: comprising polyamides
- B32B 29/02: next to a fibrous or filamentary layer
- B64C 1/066: {Interior liners}
- B64C 1/067: {comprising means for preventing icing or condensation conditions}
- H05B 3/26: heating conductor mounted on insulating base {(for transparent areas H05B3/84, H05B3/86)}
- H05B 3/34: flexible, e.g. heating nets or webs
- B32B 2260/021: Fibrous or filamentary layer
- B32B 2260/046: Synthetic resin
- B32B 2262/101: Glass fibres
- B32B 2262/106: Carbon fibres, e.g. graphite fibres
- B32B 2307/304: Insulating
- B32B 2307/718: Weight, e.g. weight per square meter
- B32B 2307/732: Dimensional properties
- B32B 2605/18: Aircraft
- B64C 2001/0072: {from composite materials}
- B64C: AEROPLANES; HELICOPTERS
- B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- H05B: ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL

## Abstract

A cladding element having a heating layer in a sandwich construction. In the case of a cladding element in a sandwich construction for an interior space of an aircraft, the cladding element includes a core layer and a first cover layer. The first cover layer forms a visible side of the cladding element. An electrically heating layer extends at least across a sub-face of the first cover layer and serves for generating heat for emission through the first cover layer is disposed between the core layer and the first cover layer.

## Claims

### Claim 1

A cladding element for an interior space of an aircraft, the cladding element comprising:
a first cover layer forming a visible side of the cladding element;
an electrically heating layer extending across at least a sub-face of the first cover layer and serving for generating heat for emission through the first cover layer;
two intermediate layers that are sandwiched between the electrically heating layer and the first cover layer;
a further intermediate layer that is positioned on an opposite side of the electrically heating layer from the two intermediate layers, such that the electrically heating layer is sandwiched directly between one of the two intermediate layers and the further intermediate layer;
at least one core layer disposed such that the electrically heating layer is sandwiched between the at least one core layer and one of the two intermediate layers; and
an electrical conductor that is electrically connected to the electrically heating layer;
wherein the two intermediate layers are formed from a fiber-composite material;
wherein a first portion of the electrical conductor is sandwiched directly between the at least one core layer and the further intermediate layer;
wherein a second portion of the electrical conductor passes through a cutout formed in the further intermediate layer, such that the second portion of the electrical conductor electrically contacts the electrically heating layer; and
wherein the first cover layer, the electrically heating layer, the at least one two intermediate layers, and the at least one core layer are arranged such that the cladding element has a sandwich construction.

### Claim 2 (depends on 1)

The cladding element according to claim 1, comprising a second cover layer that is opposite the first cover layer with respect to the electrically heating layer and the at least one core layer.

### Claim 3 (depends on 2)

The cladding element according to claim 2, wherein at least one of the first cover layer and the second cover layer is a multiple-tier layer formed from a fiber-composite material.

### Claim 4 (depends on 3)

The cladding element according to claim 3, wherein:
the fiber-composite material is a prepreg; and/or
each of the first cover layer, the at least two intermediate layers, and the second cover layer is a multiple-tier layer formed from a fiber-composite material.

### Claim 5 (depends on 4)

The cladding element according to claim 4, wherein the fiber-composite material is a prepreg.

### Claim 6 (depends on 4)

The cladding element according to claim 4, comprising a second further intermediate layer that is sandwiched directly between the at least one core layer and the second cover layer.

### Claim 7 (depends on 1)

The cladding element according to claim 1, wherein the at least one core layer contains a honeycomb core or is a honeycomb core.

### Claim 8 (depends on 1)

The cladding element according to claim 1, wherein the first cover layer is a multiple-tier layer formed from the fiber-composite material.

### Claim 9 (depends on 8)

The cladding element according to claim 8, wherein the fiber-composite material is a prepreg.

### Claim 10 (depends on 1)

The cladding element according to claim 1, wherein:
the heating layer is perforated; and/or
the heating layer contains or is a heating element that extends in a planar manner.

### Claim 11 (depends on 1)

The cladding element according to claim 1, wherein the cladding element contains at least one temperature sensor and/or at least one thermal fuse which are or is thermally coupled to the heating layer.

### Claim 12 (depends on 11)

The cladding element according to claim 11, wherein the temperature sensor is separated from the heating layer by the at least two intermediate layers.

### Claim 13 (depends on 11)

The cladding element according to claim 11, wherein the cladding element contains at least one electrical connection element for electrically connecting the heating layer and/or conductors and/or the temperature sensor and/or the thermal fuse.

### Claim 14 (depends on 13)

The cladding element according to claim 13, wherein the cladding element has at least one pocket-hole type clearance which from a rear side of the cladding element in a transverse direction leads to at least one of the connection elements and which is sealed after the connection elements have been electrically connected.

### Claim 15 (depends on 1)

The cladding element according to claim 1, wherein the heating layer is electrically contacted at two opposite peripheral regions.

### Claim 16 (depends on 15)

The cladding element according to claim 15, wherein the heating layer between the two opposite peripheral regions has at least two portions which are electrically switched in series, wherein the at least two portions differ in terms of at least one parameter.

### Claim 17 (depends on 16)

The cladding element according to claim 16, wherein the at least one parameter is a width and/or a thickness and/or an electrical resistance and/or a perforation parameter of the heating layer.

### Claim 18 (depends on 1)

The cladding element according to claim 1, wherein the cladding element is a cladding element for a location in an aircraft where there is insufficient installation space for an adequate passive thermal insulation of the interior space.

### Claim 19 (depends on 1)

The cladding element according to claim 1, wherein the at least one core layer is produced from foam.

### Claim 20

A structural part in a form of a folding mechanism for an emergency exit of an aircraft, the structural part comprising:
a metallic frame in a form of an articulated support structure to which holders and connecting tabs for the emergency exit are fastened in a mechanically stable manner;
a cladding element that is attached to the metallic frame to face an interior space of the aircraft, the cladding element comprising:
a first cover layer forming a visible side of the cladding element;
an electrically heating layer extending across at least a sub-face of the first cover layer and serving for generating heat for emission through the first cover layer;
two intermediate layers that are sandwiched between the electrically heating layer and the first cover layer;
a further intermediate layer that is positioned on an opposite side of the electrically heating layer from the two intermediate layers, such that the electrically heating layer is sandwiched directly between one of the two intermediate layers and the further intermediate layer;
at least one core layer disposed such that the electrically heating layer is sandwiched between the at least one core layer and one of the two intermediate layers; and
an electrical conductor that is electrically connected to the electrically heating layer;
wherein the two intermediate layers are formed from a fiber-composite material;
wherein a first portion of the electrical conductor is sandwiched directly between the at least one core layer and the further intermediate layer;
wherein a second portion of the electrical conductor passes through a cutout formed in the further intermediate layer, such that the second portion of the electrical conductor electrically contacts the electrically heating layer; and
wherein the first cover layer, the electrically heating layer, the two intermediate layers, and the at least one core layer are arranged such that the cladding element has a sandwich construction; and
at least one viewing window that penetrates the structural part, including the cladding element, to allow a view from the interior space of the aircraft, through the at least one viewing window, through the structural part.