Radiant heating device for an aircraft and cabin element equipped with such a device

Abstract

A radiant heating device (2) for an aircraft includes a heating layer (4) provided with at least one anode (6) and at least one cathode (8), a forward protective layer (10) and a rear protective layer (12) respectively disposed on either side of the heating layer (4), a shell (18) fixed to the forward protective layer (10), and at least one temperature sensor (26) configured to provide temperature information of the radiant heating device (2) of the forward protective layer to an external control device (9), the temperature sensor (26) comprising a thermistor having a negative temperature coefficient disposed on the rear protective layer (12) opposite the forward protective layer (10).

Description

[Technical Field]

[0001] The present invention relates to a heating device for the thermal comfort of passengers in an aircraft cabin, and to a cabin element comprising such a device. [Background technology]

[0002] Radiant electric heating devices spread heat by radiation.

[0003] Such devices generally include a heating layer and an electrode layer disposed between two insulating layers.

[0004] In order to be installed on an aircraft, the heating device must be certified for airworthiness, in particular to guarantee the safety of passengers by meeting strict fire resistance regulations.

[0005] To ensure the comfort of passengers on board the aircraft and to allow passengers to touch the heating device without risk of being burned, the temperature of the heating device must be controlled. Summary of the Invention

[0006] In light of the above, the object of the invention is to propose a heating device that is particularly fire-resistant.

[0007] An object of the present invention is to provide a radiant heating device for an aircraft, comprising a heating layer provided with at least one anode and at least one cathode, a forward protective layer and a rear protective layer respectively arranged on either side of the heating layer, and a shell fixed to the forward protective layer, wherein the radiant heating device comprises at least one temperature sensor configured to provide temperature information about the radiant heating device to an external control device.

[0008] The temperature sensor transmits the temperature information to an external control device, which can ensure the comfort and safety of passengers on board the aircraft.

[0009] Advantageously, the temperature sensor comprises a thermistor with a negative temperature coefficient arranged on the rear protective layer opposite the front protective layer.

[0010] Optionally, the shell comprises at least one fire resistant thermoplastic material, which preferably comprises acrylic and polyvinyl chloride.

[0011] Advantageously, the device comprises first fire-resistant fastening means arranged between the front protective layer and the shell.

[0012] Optionally, the first fastening means comprises a first double-sided adhesive strip, which preferably comprises fabric and vulcanized rubber.

[0013] Advantageously, the device comprises second fire-resistant fastening means arranged between the rear protective layer and the heating layer.

[0014] In one embodiment, the second fastening means comprises a second double sided adhesive strip, which preferably comprises polyethylene terephthalate and acrylic.

[0015] The forward protective layer may include polyimide and copper clad.

[0016] Optionally, the device comprises an intermediate protective layer between the heating layer and the second fixing means.

[0017] Advantageously, the device comprises a radiant heat insulating layer arranged between the second fastening means and the rear protective layer.

[0018] Another object of the invention is an aircraft cabin element comprising a control device and at least one heating device as described above, wherein a temperature sensor provides temperature information of the heating device to the control device. [Brief explanation of the drawings]

[0019] Other objects, features and advantages of the present invention will become apparent from a reading of the following description, given purely by way of non-limiting example and made with reference to the accompanying drawings, in which: [Figure 1] 1 illustrates a schematic diagram of a radiant heating device in communication with a controller according to the present invention. [Figure 2] 1 illustrates a schematic diagram of an aircraft cabin element according to the present invention; DETAILED DESCRIPTION OF THE INVENTION

[0020] 1 shows a schematic representation of a radiant heating device 2 intended for use in the interior fitting of aircraft cabins, such as airplanes and helicopters. The heating device 2 comprises several layers stacked together to form a multi-layer structure.

[0021] The heating device 2 includes a heating layer 4. The heating layer 4 is provided with at least one anode 6 and at least one cathode 8 intended to provide an interface with an electrical connection. The anode 6 and cathode 8 are associated with the heating layer 4, but are distinct from the heating layer 4. The anode 6 and cathode 8 may include, for example, a metallic ink (e.g., silver ink).

[0022] Electrical connections are made, for example by wires and connectors (not shown), to electrically connect the anode 6 and cathode 8 to the aircraft's external controls 9. The controls 9 generate an electrical current that passes through the heating layer 4, causing the heating layer 4 to emit radiant heat.

[0023] The heating layer 4 can limit the temperature of the radiated heat below a certain threshold, in particular by increasing the electrical resistance of the heating layer 4 .

[0024] For this purpose, for example, the heating layer 4 comprises a material with a positive temperature coefficient or a material with a high coefficient of thermal resistance, such as, for example, a carbon ink or a metal mixture containing copper.

[0025] In one embodiment, the heating layer 4 comprises multiple materials to increase the flexibility of the heating layer 4 and / or to allow for heating at different levels along the heating layer 4.

[0026] The heating device 2 includes a front protective layer 10 and a rear protective layer 12 provided on either side of the heating layer 4 .

[0027] By front is meant the side of the heating device 2 that is intended to face the passengers inside the aircraft.

[0028] By rear is meant the side of the heating device 2 that is intended to face a support (not shown) of the aircraft. The heating device 2 comprises, for example, two fixing elements 14 for fixing the heating device 2 to the support.

[0029] The fixing elements 14 include, for example, removable fixing clips and / or self-gripping fasteners and / or screws.

[0030] The front and rear protective layers 10, 12 provide mechanical strength and electrical and environmental protection for the heating device 2. Environmental protection corresponds, for example, to protection against humidity or temperature outside the heating device 2, or chemical protection.

[0031] The front protective layer 10 includes, for example, polyimide and copper cladding 16 .

[0032] For example, the thickness of the polyimide is 12 μm to 45 μm, and the thickness of the copper clad is 9 μm to 35 μm.

[0033] In one embodiment, the protective layer comprises Pyralux AC® material manufactured by DuPont.

[0034] The rear protective layer 12 includes, for example, polyimide.

[0035] The heating device 2 comprises a shell 18 made of plastic material fixed to the front protective layer 10 .

[0036] The shell 18 may come into contact with passengers.

[0037] To protect the passengers, the plastic shell 18 includes at least one fire-resistant thermoplastic material.

[0038] Additionally, the thermoplastic material has a high thermal conductivity to facilitate heat transfer from the heating layer 4 to the passengers, and thermal inertia to allow the plastic shell 18 to be at a comfortable temperature, high enough to ensure passenger comfort, but cool enough to be touched by passengers without risk of being burned.

[0039] The thermoplastic material is a fire resistant material, for example one that has been treated with a flame retardant coating.

[0040] Thermoplastic materials include, for example, acrylic and polyvinyl chloride, particularly plastic shell 18, which has a burn length of less than 5 mm and an average ignition time of less than 1 second in a 12-second vertical burn test, "vertical burn 12s."

[0041] In one embodiment, the thermoplastic material comprises the commercially available material Kydex 5555®.

[0042] Optionally, the heating device 2 includes a decorative layer 20, which is fixed to the plastic shell 18 and is visible to passengers inside the aircraft. The decorative layer 20 has similar properties to the plastic shell 18, particularly with regard to fire resistance.

[0043] Preferably, the plastic shell 18 is secured to the front protective layer 10 by fire-resistant first securing means 22. The first securing means 22 is, for example, flame-retardant.

[0044] The first fastening means 22 comprises, for example, a first double-sided adhesive strip.

[0045] In one embodiment, the first double-sided adhesive strip comprises a fabric covered on both sides with vulcanized rubber, for example, the thickness of the first double-sided adhesive strip is 310 μm to 350 μm.

[0046] In one embodiment, the first double-sided adhesive strip comprises the commercially available material Nitto P55®.

[0047] Preferably, the heating layer 4 is fixed to the rear protective layer 12 by fire-resistant second fixing means 24. The second fixing means 24 is, for example, flame-retardant.

[0048] The second fastening means 24 comprises, for example, a second double-sided adhesive strip.

[0049] In one embodiment, the second double-sided adhesive strip comprises polyethylene terephthalate coated on both sides with acrylic, for example, the thickness of the second double-sided adhesive strip is between 45 μm and 55 μm.

[0050] In one embodiment, the second double-sided adhesive strip comprises the commercially available material Tesa 58372®.

[0051] The heating device 2 comprises at least one temperature sensor 26 capable of supplying temperature information about the heating device 2 , in particular the temperature information of the heating layer 4 , to an external control device 9 .

[0052] The heating device 2 includes a thermistor with a negative temperature coefficient that is disposed on the rear protective layer 12 opposite the front protective layer 10 and electrically connected to an external controller 9. The external controller 9 can control the temperature of the heating device 2 in light of the temperature information.

[0053] Optionally, the heating device 2 includes an intermediate protective layer 28 disposed between the heating layer 4 and the rear protective layer 12 , for example between the heating layer 4 and the second fastening means 24 .

[0054] The intermediate protective layer 28 comprises, for example, a solvent that protects the heating layer 4 from mechanical attack.

[0055] The heating device 2 may include an insulating layer 30 that provides thermal protection against radiant heat.

[0056] This heat insulating layer 30 is arranged between the heating layer 4 and the rear protective layer 12, for example between the rear protective layer 12 and the second fastening means 24.

[0057] The heat insulating layer 30 contains, for example, a metal material so as to reflect the radiant heat emitted from the heating layer 4 and directed toward the rear protective layer 12 toward the passenger side.

[0058] Furthermore, the insulating layer 30 improves the fire robustness of the heating device 2 .

[0059] The heating device 2 may also include a rear protective layer 32 disposed on the rear protective layer 12 opposite the front protective layer 10 .

[0060] For example, the rear protective layer 32 includes an insulating foam that can limit the amount of radiant heat that escapes from the heating device 2 through the rear protective layer 12, particularly to increase radiant heat in the direction of the front protective layer 10 and therefore in the direction of the passengers.

[0061] FIG. 2 shows diagrammatically an aircraft cabin element 34 including a control device 9 and two heating devices 2 .

[0062] The control device 9 can control the temperatures of the two heating devices 2 by using the temperature information of the two heating devices 2 in particular.

[0063] For example, the cabin element 34 is an aircraft seat provided with a leg rest panel 36, a leg recess 38, and a foot housing 40.

[0064] Passengers in the aircraft can stretch their legs in the leg recesses 38 to rest on the leg rest panel 36 or insert their feet into the foot housings 40 .

[0065] The two heating devices 2 can warm the feet and / or legs of the passenger according to the passenger's posture.

[0066] In another embodiment, the cabin element 34 comprises a wall of the aircraft near the passengers, such as a raised floor of the aircraft cabin, and the heating device 2 is positioned in that wall to heat the passengers. [Explanation of symbols]

[0067] 2 Heating device 4 heating layer 6 anodes 8 cathode 9 External control device 9 Control Device 10 Front protective layer 12 Rear protective layer 14 Fixed Elements 16 Copper clad 18 shells 20 Decorative layer 22 First fixing means 24 Second fixing means 26 Temperature Sensor 28 Intermediate protective layer 30 Insulation layer 32 Back protection layer 34 Guest Room Elements 36 Panels 38 Leg recesses 40 foot housing

Claims

1. a heating layer (4) provided with at least one anode (6) and at least one cathode (8); a front protective layer (10) and a rear protective layer (12) respectively disposed on both sides of the heating layer (4); a shell (18) fixed to the front protective layer (10); A radiant heating device (2) for an aircraft, comprising: the radiant heating device (2) comprises at least one temperature sensor (26) configured to provide temperature information about the radiant heating device (2) to an external control device (9); The temperature sensor (26) comprises a thermistor having a negative temperature coefficient, disposed on the rear protective layer (12) opposite the front protective layer (10). Radiant heating device (2).

2. the shell (18) comprises at least one fire-resistant thermoplastic material; The fire resistant thermoplastic material preferably includes acrylic and polyvinyl chloride. A radiant heating device (2) according to claim 1.

3. a fire-resistant first fastening means (22) disposed between the front protective layer (10) and the shell (18); A radiant heating device (2) according to claim 1 or claim 2.

4. said first fastening means (22) comprising a first double-sided adhesive strip; The first double-sided adhesive strip preferably comprises a fabric and vulcanized rubber. A radiant heating device (2) according to claim 3.

5. a second fire-resistant fastening means (24) disposed between the front protective layer (12) and the heating layer (4); A radiant heating device (2) according to claim 1 or claim 4.

6. said second fastening means (24) comprising a second double-sided adhesive strip; The second double-sided adhesive strip preferably comprises polyethylene terephthalate and acrylic. A radiant heating device (2) according to claim 5.

7. The front protective layer (10) comprises polyimide and copper clad (16); A radiant heating device (2) according to any one of claims 1 to 6.

8. an intermediate protective layer (28) disposed between the heating layer (4) and the second fixing means (24); A radiant heating device (2) according to any one of claims 5 to 7.

9. a radiant heat insulating layer (30) disposed between the rear protective layer (12) and the second fixing means (24); A radiant heating device (2) according to any one of claims 5 to 8.

10. A control device (9); At least one radiant heating device (2) according to any one of claims 1 to 9; Equipped with The temperature sensor (26) provides temperature information about the radiant heating device (2) to the control device (9). Aircraft cabin elements.

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