DE102020206690A1 - Aircraft lighting device for an aircraft interior, cabin arrangement with the flight lighting device and aircraft with the flight lighting device and / or cabin arrangement - Google Patents

Abstract

An aircraft lighting device 1 is used for illuminating an aircraft interior, with a layer panel 2, the layer panel 2 having a glass layer 3 and a film layer 4a, the film layer 4a covering the entire surface of the glass layer 3 on one side, with a lighting device 5 for emitting light, wherein the lighting device 5 is arranged to couple the light into the layer panel 2, proposed, the glass layer 3 having a material thickness of less than 1.2 millimeters. Furthermore, a cabin arrangement with the aircraft lighting device 1 and an aircraft with the aircraft lighting device 1 and / or the cabin arrangement are proposed.

Description

The invention relates to an aircraft lighting device for an aircraft interior with the features of the preamble of claim 1. Furthermore, the invention relates to a cabin arrangement for an aircraft with the aircraft lighting device according to claim 13 and an aircraft with the features of claim 14.

On the one hand, lighting, in particular the lighting of an aircraft cabin interior, is becoming increasingly important for airlines striving for individuality, but on the other hand, aircraft manufacturers or developing suppliers are faced with the challenge of creating lighting components that meet the strict safety regulations for large aircraft, for example with regard to mechanical stability or fire protection .

A light that can be individually designed is in particular a surface light, since it offers great design options due to its surface area. For example, the surface light can easily be individually adapted to the customer's wishes through its color design or a pattern, e.g. from the airline.

Surface lights made of glass are also known, the glass serving as a surface light guide. In general, flat light guides made of, for example, PMMA are known as light guide material, but are out of the question with regard to fire behavior in aircraft cabins. Again, a surface light made of glass is defective due to its high weight and the risk of breakage.

In order to offer passengers comfort not only in business class and first class, accent lighting in aircraft cabins is known. These are often designed as indirect lighting, with the accent lighting, for example, surrounding the object to be illuminated. Such lighting is for example in the WO 03084810 A1 disclosed. This shows an aircraft window frame with indirect artificial lighting, which has a connection funnel for connection to the inside of an aircraft window, a screen that closes the window frame to the aircraft interior, a hollow cylindrical transition element made of translucent material to bridge a distance between the connection funnel and the screen, and a lighting device, which emits light on the outside of the transition element.

The invention is based on the object of creating an aircraft lighting device which is characterized by a weight-reduced and stable structure. This object is achieved by an aircraft lighting device with the features of claim 1, by a cabin arrangement with the aircraft lighting device with the features of claim 13 and by an aircraft with the aircraft lighting device and / or the cabin arrangement.

The invention relates to an aircraft lighting device for lighting an aircraft interior, in particular a passenger cabin. The aircraft lighting device is preferably designed as an aircraft cabin ceiling light, this being arranged on a cabin ceiling, for example along the entire cabin ceiling. Alternatively or optionally in addition, the aircraft lighting device is arranged on the ceiling side in a partial area of the aircraft interior, for example in the area of a board kitchen / galley, a washroom / lavatory, a door or a passage. The aircraft lighting device is preferably connected to the aircraft interior. The aircraft lighting device is preferably designed so that it can be integrated into the aircraft interior. For example, the passenger cabin has a plurality of cladding elements, the aircraft lighting device preferably being connectable to one or more cladding elements and / or being designed to be integrated into them. Alternatively or optionally in addition, the aircraft lighting device itself is designed as a cladding element for cladding in areas, e.g. an aircraft fuselage of the aircraft. The aircraft lighting device is preferably designed as accent lighting for directed lighting of an object and / or an area in the aircraft interior. Alternatively or optionally in addition, the entire aircraft interior can be illuminated by the aircraft lighting device.

The aircraft lighting device has a layer panel. The layer panel is preferably designed as a plate-shaped, multilayer component. The layer panel is preferably designed to be rectangular. The layer panel has a glass layer, in particular a transparent glass layer. The glass layer is preferably designed as a thin glass pane. The glass layer is preferably designed as a single-layer glass pane and / or glass plate. Alternatively, the glass layer is made up of several layers, for example a double-glazed layer.

Furthermore, the layer panel has a film layer, the film layer covering the entire surface of the glass layer on one side. “Covered over the entire area” is to be understood as meaning, in particular, at least 95 percent coverage of the film layer with the glass layer. The film layer covers the Glass layer on one side. The film layer is preferably arranged on the side of the glass layer which faces the aircraft interior. The film layer is preferably designed as a film layer on the front side of the layer panel and / or can be referred to as such. The film layer is preferably made of a heat-resistant and flame-retardant material, for example a heat-resistant and flame-retardant plastic. The film layer preferably has a layer thickness of at least 20 micrometers, preferably of at least 30 micrometers, in particular of at least 40 micrometers.

The aircraft lighting device has a lighting device for emitting light, in particular visible light. The illuminant device preferably has at least one illuminant, a plurality of illuminants, for example light-emitting diodes (LED), preferably contributing jointly, for example as an LED array, to illuminating the aircraft interior. The illuminant device is preferably designed to be connectable to an on-board network of the aircraft for supplying energy.

The lighting device is arranged to couple the light into the layer panel. The illuminant device or preferably at least the illuminant of the illuminant device is connected to the layer panel in such a way that the light can be coupled into the glass layer and / or the film layer. Coupling is to be understood as radiating through and / or at least introducing the light into the layer panel for guiding the light within the layer panel.

The layer panel preferably has a luminous surface for coupling out the light. The luminous area is preferably formed on the side which faces the aircraft interior. The luminous area is preferably a visible area. The luminous surface is in particular that section of the aircraft lighting device which is perceived by a passenger as a light-emitting component and / or as a light source in the aircraft interior. The light coupled in by the illuminant device is emitted into the aircraft interior via the luminous surface. The luminous area is preferably arranged on the side of the film layer and / or is formed by the film layer itself and / or at least by one or more sections of the film layer. For example, the film layer has a pattern which is characterized by translucent and opaque sections. The light is only emitted into the aircraft interior through the translucent sections. This creates an individual light image and / or an illuminated pattern for the passenger.

According to the invention it is provided that the glass layer has a material thickness of less than 1.2 millimeters. The glass layer preferably has a material thickness of less than 1.0 mm, particularly preferably less than 0.8 mm. The layer panel with a glass layer and a film layer preferably has a total thickness of less than 1.5 mm, preferably less than 1.0 mm. As a result, the layer panel is designed as a thin component of the aircraft lighting device, as a result of which the layer panel has a small installation depth. The glass layer, the “thin” glass layer (<1.2mm), is stabilized and / or supported in particular by the film layer so that, for example, bending of the glass layer is and / or can be avoided. Alternatively or optionally in addition, the film layer is arranged on the glass layer in order to hold the fragments together and / or to support them if the glass layer breaks, so that they are protected from falling into the aircraft interior.

The aircraft lighting device, which is preferably designed as a surface light, has a surface light guide, this being formed by the layer panel. The illuminant device is preferably arranged to couple the light into the surface light guide. The flat light guide preferably guides the light within the flat light guide, the light being distributed and / or being able to be distributed throughout the flat light guide. The surface light guide has the luminous surface, the light coupled into the surface light guide being decoupled via the luminous surface and emitted and / or emitted into the aircraft interior. The luminous means device preferably couples the light in a section of the surface light guide, the surface light guide guiding the light from the section into another section with the luminous surface. As a result, the lighting means device, which requires a larger installation space than the thin layered panel, can be accommodated in a very space-saving manner, for example on an edge section. The layer panel, or the surface light guide, redirects the light. This is to be understood as a single or multiple deflection of the light within the layer panel and / or an entrance angle and an exit angle of the light, which differ significantly.

Alternatively, the aircraft lighting device is designed as an effect light, the layer panel forming a diffusing light disk. The illuminant device is arranged to couple the light into the light diffuser, wherein the light diffuser scatters the light over the luminous surface into the aircraft interior, in particular scatters it uniformly. The light shines through the light diffuser. Shining through is to be understood as meaning that the light is almost unhindered and / or passes the lens without being distracted. The uniform scattering of the light into the aircraft interior is not to be understood as a deflection. For example, the light diffuser is designed to be translucent, the light diffuser being partially transparent to the light. The glass layer and / or the film layer are preferably designed to be translucent. The light diffuser creates a uniform illumination image of the illuminated area and / or the aircraft interior for the passenger.

It is advantageous that the essentially common structure of the layered panel creates an aircraft lighting device which is advantageously suitable for at least two different lighting concepts, which is characterized by its weight optimization and a low installation depth. It is also advantageous that the film layer improves the mechanical stability of the glass layer so that it can be used in large aircraft. It is also advantageous that the film layer and the essentially large-area illuminated area can be individually designed, e.g. by the customer or the airline using patterns and / or colors. It is particularly advantageous that the structure of the layered panel has qualified materials approved for aviation, as a result of which a heat-resistant and flame-retardant aircraft lighting device is created. The break resistance of the glass layer (ball impact test) required for aviation is given by the advantageous complete coverage with the film layer.

In a preferred embodiment of the invention it is provided that the layer panel has a luminous area for coupling out the light of at least 0.1 m ² . The luminous area preferably has at least 0.2 m ² , in particular at least 0.3 m ² . Due to the luminous area (> 0.1 m ² ), the aircraft lighting device is preferably designed as a ceiling light in the aircraft interior. For example, the aircraft lighting device is arranged in the middle of a ceiling panel of the passenger cabin, the aircraft lighting device extending and / or being formed in a section or along the entire passenger cabin. The film layer has a supporting function so that a large luminous area (> 0.1m ² ) can be realized.

In a particularly preferred embodiment of the invention it is provided that the layer panel has a further film layer, the further film layer covering the entire surface of the glass layer on an opposite side. In the case of the further film layer as well, “completely covered” is preferably to be understood as covering at least 95 percent. The further film layer is arranged on the side of the glass layer facing away from the aircraft interior, wherein the further film layer is preferably designed as a rear-side film layer and / or can be viewed as such. The further film layer is preferably made of a heat-resistant and flame-retardant material, e.g. a heat-resistant and flame-retardant plastic. The further film layer preferably has a layer thickness of at least 80 micrometers, preferably of at least 100 micrometers, in particular of at least 120 micrometers. The layer panel has the film layer and the further film layer, the glass layer being arranged between the two film layers. The film layer and / or the further film layer are designed to support the glass layer, so that the mechanical stability of the glass layer or of the entire structure of the layer panel is improved. The two film layers are preferably designed as self-adhesive film layers. Alternatively, one or both film layers are bonded to the glass layer by a thermal process.

In a preferred embodiment of the invention it is provided that at least one film layer has an optical diffuser pattern in order to scatter the light coupled into the layer panel into the aircraft interior. The film layer preferably has the optical diffuser pattern. The diffuser pattern is preferably arranged on the side of the layer panel facing the aircraft interior. Alternatively or optionally in addition, the further film layer has the optical diffuser pattern, the diffuser pattern being arranged on the side of the layer panel facing away from the aircraft interior. When the coupled light hits the diffuser pattern, it is refracted and scattered into the aircraft interior by a diffuse reflection. The diffuser pattern is preferably designed as an individual print pattern for partially scattering the light into the aircraft interior. For example, translucent sections of the film layer and / or the further film layer form the diffuser pattern, only the translucent sections being perceived and / or perceptible to the passenger as luminous objects and / or accents. It is advantageous that an individual pattern, for example a lettering or logo of an airline, which is designed as a diffuser pattern, is illuminated by the partial scattering of the light and appears to be emphasized to the passenger. Alternatively, the diffuser pattern is formed over the entire area on one or both film layers. In other words, the film layer and / or the further film layer is preferably designed as a diffusion film and / or diffuser film.

In a preferred embodiment of the invention it is provided that at least one film layer is designed as a light-reflecting film. The further film layer, which is arranged on the opposite side or on the side of the layer panel facing away from the aircraft interior, is preferably designed as the light-reflecting film. The luminous surface is preferably formed on the opposite side of the light-reflecting film, the light hitting the light-reflecting film being reflected and deflected in the direction of the luminous surface for decoupling and / or being deflectable. The light-reflecting film preferably has a light-reflecting pattern and / or a light-reflecting coating which is designed to deflect the light, the pattern and / or the coating being at least partially, but preferably over the entire area and / or continuously repeating. It is advantageous that the light-reflecting film also scatters the coupled-in light within the layer panel, so that when the layer panel is designed as a surface light guide, the light is evenly distributed so that the lighting device can be operated with a low luminosity. This creates an aircraft lighting device which is characterized by low energy consumption.

In a preferred embodiment of the invention it is provided that at least one film layer is designed as a splinter protection film. The further film layer is preferably designed as the splinter protection film, the splinter protection film being arranged on the opposite side of the glass layer. Both film layers are particularly preferably designed as a splinter protection film on both sides of the glass layer and / or have a double or multiple function. The other functions are preferably the functions already mentioned above, e.g. to improve the mechanical stability of the layered panel and / or to reflect the light. If the glass layer is damaged or if the glass layer is brittle, the task of the splinter protection film is to at least reduce, preferably prevent, the escape of fragments of the glass layer, e.g. glass splinters. This is to prevent splinters of glass falling on passengers and injuring them.

In a preferred embodiment of the invention it is provided that at least one film layer has a print coating for generating an optical pattern. The film layer preferably has the print coating on the side facing the interior of the aircraft. The print coating is preferably in the form of a color print coating and / or a lacquer finish for generating an optical pattern, for example a lettering or logo, on the film layer and / or the further film layer. The printing coating is preferably designed to be at least partially translucent. Alternatively, the print coating is designed to be opaque, so that only those sections of the luminous surface that are not covered with the print coating shine. Alternatively, it is conceivable that the pressure coating forms the optical diffuser pattern and / or is designed as such. For example, the print coating is designed to be translucent in order to scatter the light coupled into the layer panel into the aircraft interior. It is also conceivable that the print coating is arranged between the glass layer and the further film layer. Here, the print coating can have the function as an optical pattern, as a diffuser pattern and / or for reflecting the light. The pattern, e.g. a repeating point pattern, reflects the incident light and is designed to be visible to the passenger as a luminous object or accent. It is advantageous that the printing of at least one film layer with the print coating creates a further design option, which can also be emphasized by the illumination of the aircraft lighting device.

In a preferred structural embodiment of the invention it is provided that the layer panel is irradiated with light from the side of the layer panel facing away from the aircraft interior in the direction of the side of the layer panel facing the aircraft interior. The light preferably shines through the layer panel unhindered or is at least only partially prevented and / or deflected from it. The aircraft lighting device preferably has an intermediate space, the intermediate space being arranged on the side of the layered panel facing away from the aircraft interior, and wherein the intermediate space is separated from the aircraft interior by the layered panel. The illuminant device is preferably arranged to emit the light into the intermediate space, the light shining through the layer panel from the intermediate space and being emitted and / or being able to be emitted into the aircraft interior. In this structural configuration, the film layer is preferably designed with a diffuser pattern, e.g. a full-surface translucent pattern, and the further film layer as a splinter protection foil, in particular as a transparent and / or translucent splinter protection foil. The light can preferably be coupled into the layer panel via the splinter protection film and shines through the layer panel in the direction of the film layer with a diffuser pattern.

The aircraft lighting device preferably has a frame support for receiving the layered panel, the lighting device being arranged on and / or in the frame support is integrated into the frame support. The frame support is preferably designed in two or more parts, the frame support having a support part and a cover part. The carrier part is preferably connected to the layer panel, for example via an adhesive connection. The carrier part is designed, for example, as a circumferential, open frame and essentially has an outer contour and / or an outer contour of the layered panel. The layer panel is preferably connected to the edge of the carrier part, preferably glued, with a connection area for connecting the two parts having an area of less than 0.05 m ² .

The illuminant device is preferably received by the cover part and / or integrated in it. The cover part is preferably designed as a cover that is closed on one side and is connected to the carrier part, preferably via a screw connection. The frame support preferably forms the intermediate space with the carrier part and with the cover part and the layered panel.

In a preferred further development of the invention it is provided that the layer panel is U-shaped and / or horseshoe-shaped. In particular, the luminous area is U-shaped and / or horseshoe-shaped. The layer panel has in particular two symmetrical legs, the two legs forming a horseshoe that is open on one side. "U-shaped and / or horseshoe-shaped" means that when the aircraft lighting device is viewed in an installed state in the aircraft interior, e.g. on the cabin ceiling, the layered panel and / or the luminous surface is perceived as a curved and / or curved light source. The layer panel preferably has a width, in particular a width of one of the legs, of more than 150 mm, preferably more than 250 mm. It is advantageous that the U-shaped and / or horseshoe-shaped design of the layer panel increases the mechanical stability so that the layer panel manages without an additional support structure, which results in cost savings in production.

In an alternative structural embodiment of the invention it is provided that the luminous communication device is arranged to couple the light into the layer panel at the edge, the layer panel guiding the coupled light within the layer panel. For this purpose, the layer panel is preferably designed as a flat light guide. The illuminant device is preferably arranged on an edge section of the layer panel, in particular the rectangular layer panel. For example, the illuminant device couples the light into the layer panel at the end and / or at the edge, the layer panel guiding the light out of the edge section. In particular, the light can be guided from the edge section to the luminous surface. In this structural configuration, the aircraft lighting device is preferably designed as a surface light and extends in a section or in the entire aircraft interior, for example on the cabin ceiling. The edge-side coupling of the light or the edge-side arrangement of the illuminant device enables a long aircraft lighting device to be created that extends over several meters, preferably more than 2 meters, and / or wide, over more than 0.4 meters, preferably more than 1 meter . For example, the illuminant device has an LED array as the illuminant and / or is designed as such, the illuminant device extending over the entire side length of the layer panel at the edge and coupling the light into the layer panel over the entire side length.

In a particularly preferred further development of the invention, it is provided that the aircraft lighting device has a carrier device. The carrier device is preferably designed as a plate-shaped and / or dimensionally stable component. The carrier device is preferably of rectangular design. The carrier device is connected over the entire surface to the layered panel, the carrier device being arranged on the side of the layered panel facing away from the aircraft interior. The layer panel is preferably connected to the carrier device via an adhesive connection. The adhesive connection is preferably designed as an adhesive layer and is connected over the entire surface to the carrier device and the layer panel. The further film layer is preferably arranged between the glass layer and the carrier device. In this structural configuration, the further film layer is particularly preferably designed at least as a light-reflecting film. This prevents a direct view of the carrier device, e.g. by the passenger in the flight interior. It is advantageous that the full-surface connection of the layer panel to the carrier layer improves the mechanical stability of the layer panel and / or of the entire structure of the aircraft lighting device, so that, for example, bending of the “thin” layer panel is prevented. This enables the aircraft lighting device to be implemented as a “wide” and / or large area light.

In a preferred further development of the invention it is provided that the carrier device is designed as a fiber composite component, for example as a prepreg, or as a sandwich component. The sandwich component is preferably included as a multi-part and / or multi-layer composite component For example, a honeycomb core and / or a foam core formed as a carrier. In particular, the carrier device is designed as a dimensionally stable and flame-retardant component approved for aviation. Alternatively, it is conceivable that the carrier device is formed by a lining panel of the aircraft in the aircraft interior, the layer panel being glued directly to the lining panel, for example the ceiling panel. The carrier device preferably has a material thickness of less than 20 mm, in particular less than 15 mm, in particular less than 10 mm.

The aircraft lighting device preferably has a cover device for shielding the light, the cover device covering at least the lighting means device in the edge section. The cover device is preferably designed as a multi-part cover. The covering device can be seen as framing the layered panel, the covering device having the task and / or being designed to at least partially shield the light of the illuminant device from the aircraft interior, so that the light is only emitted and / or can be emitted into the aircraft interior via the layered panel is. For example, the illuminant device is connected to the cover device and / or is carried by it. Alternatively or optionally in addition, the covering device is arranged on the edge of the layered panel in such a way as to support the layered panel and the carrier device and / or to connect them to a surrounding structure, e.g. the cabin ceiling.

The layer panel, which is connected over the entire surface to the carrier device, preferably has a width of at least 300 mm, in particular of at least 350 mm. “Width” is preferably to be understood as a short side of the rectangular layered panel.

Another object of the invention is a cabin arrangement for an aircraft with the aircraft lighting device as described above. The cabin arrangement is preferably designed as one or more objects in an aircraft interior, as a cabin module and / or as the passenger cabin itself. The cabin arrangement preferably has a plurality of aircraft lighting devices. The plurality of aircraft lighting devices are preferably connected to one another for common lighting of the aircraft interior. For example, the aircraft lighting devices are modular. The one or more aircraft lighting devices are preferably arranged on a cabin ceiling of the cabin arrangement, the aircraft lighting device illuminating and / or illuminating the cabin structure surrounding the cabin ceiling, e.g. overhead lockers, and / or the entire aircraft interior.

Another object of the invention is an aircraft with the aircraft lighting device and / or the cabin arrangement with the aircraft lighting device as described above. The aircraft is preferably designed as a large aircraft and / or a passenger aircraft for civil aviation. The aircraft preferably has a fuselage with an aircraft interior, the aircraft interior preferably being lined and / or designed with a passenger cabin for transporting passengers. The aircraft lighting device is arranged in the aircraft interior, the aircraft lighting device preferably being connected to and / or integrated in the passenger cabin. The aircraft preferably has the aircraft lighting device for illuminating the aircraft interior, this particularly preferably being designed as a ceiling light in the aircraft interior.

• 1 einen schematischen Schichtaufbau eines Schichtpaneels für eine Flugzeugbeleuchtungsvorrichtung als ein erstes Ausführungsbeispiels;
• 2 in einer Schnittdarstellung einen Ausschnitt der Flugzeugbeleuchtungsvorrichtung mit dem Schichtpaneel aus 1 als ein konstruktives Ausführungsbeispiel;
• 3a einen schematischen Schichtaufbau des Schichtpaneels als ein weiteres Ausführungsbeispiel;
• 3b eine Vorderansicht der Flugzeugbeleuchtungsvorrichtung als ein weiteres konstruktives Ausführungsbeispiel mit dem Schichtpaneel aus 3a;
• 3c eine Schnittdarstellung der Flugzeugbeleuchtungsvorrichtung aus 3b.

Further features, effects and advantages of the invention emerge from the following description of a preferred exemplary embodiment of the invention and the attached figures. Show:

• 1 a schematic layer structure of a layer panel for an aircraft lighting device as a first exemplary embodiment;
• 2 in a sectional view a detail of the aircraft lighting device with the layer panel 1 as a constructive embodiment;
• 3a a schematic layer structure of the layer panel as a further embodiment;
• 3b a front view of the aircraft lighting device as a further structural embodiment with the layer panel from 3a ;
• 3c a sectional view of the aircraft lighting device 3b .

The 1 shows a schematic layer structure of a layer panel 2 for an aircraft lighting device 1 for illuminating an aircraft interior of an aircraft (not shown).

The layered panel 2 has several layers which are connected to one another in an assembly state, for example by a joining process. The viewing panel has a glass layer 3 and a film layer 4a and another layer of film 4b on, with the two layers of film 4a , b each on opposite sides of the glass layer 3 are arranged. The film layer 4a is on a side of the glass layer facing the aircraft interior 3 arranged, the side being designed as a visible side for a passenger in the aircraft interior. The film layer 4a has, for example, a diffuser pattern (not shown). Alternatively, there is the foil layer 4a designed as a diffuser film.

The other layer of film 4b is opposite the visible side on the glass layer 3 arranged, the further film layer 4b for example, a greater material thickness than the film layer 4a having. For example, the further film layer 4b a material thickness of at least 100 micrometers, the film layer 4a has a material thickness of at least 30 micrometers, but less than 80 µm. The other layer of film 4b is designed, for example, as a splinter protection film, the splinter protection film in the event of breakage of the glass layer 3 Holds them together and / or supports them so that no fragments, for example glass splinters, can get into the aircraft interior. The film layer 4a and the further layer of film 4b perform the function together as the film layer 4a on the visible side also if the glass layer breaks 3 Holds back fragments. Another common function of the two layers of film 4a , b is the mechanical stability of the layer structure of the layered panel 2 or the glass layer 3 to increase. To use the layered panel 2 In an aircraft interior, the required tests for long glass elements, for example the “Ball Impact Test” regulated in AMC25.603 (a), must be passed in order to obtain approval. In addition, the provisions on fire behavior must be complied with or a fire test and heat resistance must be. The glass layer 3 is a non-combustible material and is therefore particularly suitable with the two layers of film 4a , b offer the necessary stability and break resistance.

The glass layer 3 has a material thickness of less than 1.2mm. This "thin" formation of the glass layer 3 is possible because the two layers of film 4a , b the glass layer 3 support.

The other layer of film 4b is also designed as a light-reflecting film, the film layer 4b is designed for example opaque. The layered panel 2 has multiple print coating 9a , b on, the print coatings 9a , b on the film layer 4a and the further film layer 4b are arranged. The print coatings 9a , b are for example for the optical design of the layered panel 2 on the two layers of film 4a , b applied, for example the print coatings 9a , b are additionally designed as a diffuser pattern.

The layered panel 2 is designed for coupling in light, the coupled light within the glass layer 3 is directed. At least one or both layers of film 4a , b are formed the light back out of the layered panel 2 , for example by diffuse reflection, and to emit them into the aircraft interior. The other layer of film 4b additionally reflects the light, whereby the film layer 4a is formed on the visible side as a luminous surface for coupling out the light. The luminous area is at least 0.1 m ² , with the coupling out of the light over the entire area or only in a section, for example in the area of the film layer 4a without print coating 9a , takes place.

According to a first exemplary embodiment, the layer panel is 2 for the aircraft lighting device 1 formed, the aircraft lighting device 1 being a carrier device 10 having. In the 1 is only the carrier device 10 as part of the aircraft lighting device 1 shown. The carrier device 10 is designed as a sandwich component with several layers and a centrally arranged honeycomb core. The carrier device 10 has a greater material thickness than the layered panel 2 on. For example, the carrier device 10 a total material thickness of at least 5mm. The aircraft lighting device 1 has an intermediate layer 11 for fastening the layered panel 2 on the carrier device 10 . The intermediate layer 11 is designed, for example, as an adhesive layer, the adhesive layer having the necessary strength and necessary fire behavior for use in aircraft. The carrier device 10 is particularly in the case of a large-area configuration of the aircraft lighting device 1 needed to make the glass layer 3 to stabilize and, for example, to suppress a high relative displacement in the center in the event of vibrations. This visual structure of the layered panel described above 2 with the carrier device 10 is designed for dimensions of at least 300mm width, for example.

In the 2 is the aircraft lighting device 1 shown, the aircraft lighting device 1 the layered panel 2 with the layer structure from the 1 having. The 2 shows a section of the aircraft lighting device 1 in a sectional view. The layer panel 2 is with the carrier device 10 over the intermediate layer 11 fully connected. The layer panel 2 is designed in the direction of the aircraft interior and has a luminous area A in the same direction.

The aircraft lighting device 1 has a lighting device 5 to emit light. The lighting device 5 has one or more illuminants 6a , e.g. LED, on, where the bulbs 6a in the 2 are only indicated. The lighting device 5 has a lamp holder 6b on, with the bulbs 6a on the lamp holder 6b are arranged. The lighting device 5 is the edge of the layered panel 2 arranged, the illuminant carrier 6b for example via an adhesive connection with an edge section RA of the layered panel 2 connected is. The lighting device 5 is below, on that of the carrier device 10 opposite side, of the layered panel 2 connected or glued to this. The edge section RA of the layered panel 2 is, for example, at least 15mm, preferably at least 20mm, in size. The lighting device 5 is arranged as described to shine light into the laminated panel 2 to couple.

The aircraft lighting device 1 has a cover device 12th on. The cover device 12th has a cover panel 13a and a cover bracket 13b on. The cover panel 13a spans and / or covers the edge section RA of the layer panel 2 and the lighting device 5 so that they are shielded from the aircraft interior. The covering device 12th is opaque. Therefore, the light for illuminating the aircraft interior has to go through the layered panel 2 are coupled. The layered panel 2 guides the light from the edge section RA within the layer panel 2 to the luminous area A, with the light coming out of the viewing panel via the luminous area A 2 is decoupled and / or can be decoupled. The cover carrier 13b is with the carrier device 10 connected, the cover device 12th the "layer package" (layer panel 2 and carrier device 10 ) pinched on both sides and / or at the edge.

The 3a shows a greatly simplified structure of the layered panel 2 for another embodiment. The layered panel 2 has a simpler structure than in 1 shown on. The layer panel 2 exhibits the glass layer 3 on, with the glass layer 3 has a material thickness of less than 1.2 millimeters. The layer panel 2 exhibits the film layer 4a and the further layer of film 4b on, the film layer 4a on the side of the glass layer facing the aircraft interior 3 is arranged, the further film layer 4b on the opposite side of the glass layer 3 is arranged. Furthermore, the layer panel 2 an adhesive layer 7th on, the adhesive layer 7th on the opposite side between the glass layer 3 and another layer of film 4b is designed to connect this. This simplified structure without an additional support structure, for example through the carrier device 10 , is for example for laminated panels 2 formed with a dimension of less than 300mm width. The other layer of film 4b is as a clear anti-shatter film and the film layer 4a formed with a diffuser pattern.

The 3b shows such an aircraft lighting device 1 with the layer panel 2 out 3a , the layered panel 2 and / or the aircraft lighting device 1 is U-shaped and / or horseshoe-shaped. The aircraft lighting device 1 is isosceles and has two legs. The layered panel 2 has the luminous area A, the aircraft lighting device 1 emits the light, for example, over the entire U-shaped luminous area A into the aircraft interior. Alternatively or optionally in addition, the layer panel has 2 and / or the luminous area A has a print coating applied in sections, for example an opaque pattern, the light either only outside the pattern or only inside the pattern (negative pattern) being emitted into the aircraft interior.

The 3c shows in a sectional view (AA) 3b who have favourited U-shaped and / or horseshoe-shaped aircraft lighting device 1 , the sectional view (AA) being made through one of the two legs. The aircraft lighting device 1 has a frame support 8th on being the frame support 8th circumferentially following the U-shaped contour is formed. The frame support 8th is formed closed on one side and with the layer panel 2 connected. The frame support carries the layered panel 2 , whereby these are connected, for example, via a narrow, circumferential adhesive connection. For example, the adhesive connection has an adhesive area of less than 0.1 m ² . The frame support 8th is designed in two parts, the frame support 8th a support part 14a and a cover part 14b having. The support part is the part of the frame support 8th , which with the layer panel 2 is connected, the cover part 14b the frame support 8th closes on one side. For example, the lighting means device 5 (not shown) with the cover part 14b connected, the illuminant device 5 emits the light into a space D. The intermediate space D is on the side of the layer panel facing away from the aircraft interior 2 arranged. The space D is through the frame support 8th and the layered panel 2 designed as a closed space. The lighting device 5 is arranged in such a way that the light is emitted into the space and from there the layered panel 2 shines through. In this advantageous embodiment, the layer panel must 2 guide the light only from an edge section RA to the luminous area A.

List of reference symbols

1

Aircraft lighting device

2

Layer panel

3

Glass layer

4a

Foil layer

4b

another layer of film

5

Lighting equipment

6a

Bulbs

6b

Lamp holder

7th

Adhesive layer

8th

Frame support

9a, b

Print coating

10

Carrier device

11

Intermediate layer

12th

Cover device

13a

Cover panel

13b

Cover carrier

14a

Carrier part

14b

Cover part

QUOTES INCLUDED IN THE DESCRIPTION

This list of the documents listed by the applicant was generated automatically and is included solely for the better information of the reader. The list is not part of the German patent or utility model application. The DPMA assumes no liability for any errors or omissions.

Patent literature cited

• WO 03084810 A1 [0005]

Claims (14)

Aircraft lighting device (1) for illuminating an aircraft interior, with a layer panel (2), the layer panel (2) having a glass layer (3) and a film layer (4a), the film layer (4a) covering the entire surface of the glass layer (3) on one side covered, with a lighting device (5) for emitting light, the lighting device (5) being arranged to couple the light into the layer panel (2), characterized in that the glass layer (3) has a material thickness of less than 1.2 millimeters having. Aircraft lighting device (1) according to Claim 1 , characterized in that the layer panel (2) has a luminous surface (A) for coupling out the light of at least 0.1 m ² , preferably of at least 0.2 m ² , in particular greater than 0.3 m ² . Aircraft lighting device (1) according to Claim 1 or 2 , characterized in that the layer panel (2) has a further film layer (4b), the further film layer (4b) completely covering the glass layer (3) on an opposite side. Aircraft lighting device (1) according to one of the preceding claims, characterized in that at least one film layer (4a, b) has an optical diffuser pattern in order to scatter the light coupled into the layered panel (2) into the aircraft interior. Aircraft lighting device (1) according to one of the preceding claims, characterized in that at least one film layer (4a, b) is designed as a light-reflecting film. Aircraft lighting device (1) according to one of the preceding claims, characterized in that at least one film layer (4a, b) is designed as a splinter protection film. Aircraft lighting device (1) according to one of the preceding claims, characterized in that at least one film layer (4a, b) has a printing coating (9a, b) for generating an optical pattern. Aircraft lighting device (1) according to one of the preceding claims, characterized in that the lighting device (5) is arranged to light the layer panel (2) from the side of the layer panel facing away from the aircraft interior in the direction of the side of the layer panel (2) facing the aircraft interior radiate through. Aircraft lighting device (1) according to Claim 8 , characterized in that the layer panel (2) is U-shaped and / or horseshoe-shaped. Aircraft lighting device (1) according to one of the Claims 1 to 7th , characterized in that the luminous communication device (5) is arranged to couple the light into the layer panel (2) at the edge, the layer panel (2) guiding the coupled light inside the layer panel (2). Aircraft lighting device (1) according to Claim 10 , characterized in that the aircraft lighting device (1) has a carrier device (10), the carrier device (10) being connected over the entire surface to the layer panel (2), the carrier device (10) on the side of the layer panel (2) facing away from the aircraft interior. is arranged. Aircraft lighting device (1) according to Claim 11 , characterized in that the carrier device (10) is designed as a fiber composite component or as a sandwich component. Cabin arrangement for an aircraft, characterized by the aircraft lighting device (1) according to one of the preceding claims. Aircraft characterized by the aircraft lighting device (1) according to the Claims 1 to 12th and / or the cabin arrangement according to Claim 13 .

Images