Abstract:
The description covers cabin components for aircraft, which can be produced with a sandwich structure and may have the components  1003  for signal and/or power transmission. The cabin components in this case have at least two prepreg layers  1001, 1005  and, for example, a honeycomb layer  1002 , which can be connected to one another by pressing and heating. Furthermore, electrical and/or optical signal paths are shown on cabin components, which can be produced by positioning them there or printing. In addition, according to the description, signal and/or power transmission can take place beyond the boundary of cabin components, by means of a transmitter/receiver path.

Description:
FIELD OF THE INVENTION 
     The present invention relates to a method for fitting a cabin component for an aircraft, to a cabin component for an aircraft and to a system for fitting in an aircraft. 
     BACKGROUND TO THE INVENTION 
     Cabin components for fitting in an aircraft are known in the prior art. It is also known for components for signal transmission and power transmission to be arranged on cabin components. 
     SUMMARY OF THE INVENTION 
     Until now, cabin components with electrical and/or electronic items arranged on them have been fitted sequentially, that is to say the cabin components within an aircraft have been fitted first of all, and the electronic, electrical or optical components have been firmly fitted to or in the cabin components. This can result in a multiplicity of successive work steps, which can lengthen the time to produce the aircraft. Furthermore, after the cabin components have been fitted, it is often necessary to adapt or to modify the arrangement of the electrical and/or optical signal paths, which can result in delays to the production process. 
     One object is therefore to allow cabin components to be fitted more quickly and more easily within an aircraft in which case, a further aim of the invention is to make it possible to react flexibly to requirements which result at short notice relating to the arrangement of electrical and/or optical signal paths which are arranged adjacent to or on cabin components. 
     As a first embodiment of the invention, a method is provided for fitting a cabin component for an aircraft, comprising the following steps: 
     arrangement of a sandwich structure comprising a first honeycomb for mechanical stiffening, a first prepreg layer above the first honeycomb and a second prepreg layer below the first honeycomb, arrangement of a component for signal and/or power transmission to or within the sandwich structure and heating and pressing of the sandwich structure. 
     According to the invention, before the heating and pressing of a sandwich structure with prepreg layers within the sandwich structure, respectively required electronics or respectively required electronic components or other components, such as plug connectors or optical waveguides, can be arranged on or within the sandwich structure. This makes it possible to produce a prefabricated cabin component after heating and pressing, thus allowing faster fitting of the cabin component, including corresponding electrical and/or electronic items. 
     A cabin component for an aircraft is provided as a second embodiment, comprising: a first honeycomb for mechanical stiffening, a first prepreg layer, a second prepreg layer, a component, wherein the cabin component can be produced using the above-described method. 
     A method for fitting a cabin component for an aircraft is provided as a third embodiment of the invention, comprising the following steps: positioning an optical or electrical path on the cabin component. 
     Positioning optical or electrical paths on a cabin component by, for example, printing or rolling allows an electrical or optical path to be fitted quickly and flexibly. This makes it possible to react flexibly to restrictions to the fitting of the cabin components within an aircraft or which restrictions may result only during the fitting process. 
     A system for fitting in an aircraft is provided as a fourth embodiment of the invention, comprising: a transmitter for signal emission and/or power emission and a receiver for signal reception and/or power reception, wherein the transmitter is arranged on a first cabin component for an aircraft, and the receiver is arranged on a second cabin component for an aircraft, and wherein the first cabin component and the second cabin component are different. 
     A transmitter/receiver path for transmission of power and/or information or signals makes it possible to cover spatial distances between cabin components which can result, for example, only when the cabin components are being fitted within the aircraft. A transmitter/receiver path therefore represents a flexible possible way to connect two or more spatially separated cabin components to one another for signalling and power transmission. 
     According to one exemplary embodiment of the invention, a method is provided, wherein the component is arranged above the first prepreg layer. 
     In a further embodiment according to the invention, a method is provided, wherein a second honeycomb is arranged below the first honeycomb, wherein the first honeycomb and the second honeycomb are arranged between the first prepreg layer and the second prepreg layer, and wherein the component is arranged between the first honeycomb and the second honeycomb. 
     The arrangement of the component between two honeycombs leads to encapsulation on all sides, for example of an electrical circuit, as a result of which there is no need to arrange further protection against mechanical loading, for example a housing. 
     According to a further exemplary embodiment of the present invention, a method is provided, wherein the component is arranged within a housing. 
     The arrangement of the component within a housing provides protection against mechanical and thermal loading during the pressing and heating process. 
     According to one exemplary embodiment of the invention, a method is provided, wherein an elastomer film for vibration damping is arranged between the first honeycomb and the second honeycomb. 
     An arrangement of an elastomer film between the honeycombs can lead to damping of mechanical vibration, thus allowing the component which is fitted in the sandwich structure to be protected against twisting. 
     In a further embodiment according to the invention, a method is provided, wherein the component is an electronic circuit, a printed circuit board, an electrical conductor track, an optical waveguide or a plug connector. 
     According to a further exemplary embodiment of the present invention, a method is provided, wherein the optical path is a carbon or a glass tape, and/or wherein an electrical path is positioned by printing an electrical conductor track. Carbon is a carbon-fibre-reinforced plastic. 
     An arrangement of electrical and/or optical paths by positioning or printing allows flexible matching to circumstances on the basis of the cabin components to which the paths are fitted, and which circumstances may, for example, occur only at short notice during final assembly. 
     One idea of the invention can be considered to provide cabin components for an aircraft which already have integrated components for signal and/or power transmission. The cabin components can be produced by heating and pressing a plurality of prepreg and honeycomb layers, in which case the components can be arranged between individual layers. A further aspect according to the invention represents the application of optical or electrical paths to cabin components, thus allowing appropriate optical and/or electrical paths to be arranged quickly and flexibly. Furthermore, according to the invention, transmitters and receivers for signal transmission and power transmission can be arranged on different cabin components, in order to allow spatial distances to be bridged between different cabin components. 
     The individual features may, of course, also be combined with one another, which may in some cases also result in advantageous effects which go beyond the sum of the individual effects. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       Further details and advantages of the invention will become clear from the exemplary embodiments which are illustrated in the drawings, in which: 
         FIG. 1  shows a schematic illustration of optical signal transmission, 
         FIG. 2  shows a schematic illustration of inductive power transmission, 
         FIG. 3  shows the positioning of optical or electrical paths, 
         FIG. 4  shows a conductor track which has been positioned, 
         FIG. 5  shows the printing of electrical conductor tracks, 
         FIG. 6  shows a schematic illustration of a printed conductor track, 
         FIG. 7  shows a schematic illustration of a pressed-in optical waveguide, 
         FIG. 8  shows a schematic illustration of a pressed-in plug connector, 
         FIG. 9  shows an illustration of daisy-chain integration, 
         FIG. 10  shows an illustration of a sandwich structure before the pressing process, 
         FIG. 11  shows a schematic illustration of an external interface, 
         FIG. 12  shows a housing for protection of a board, 
         FIG. 13  shows a schematic illustration of a sandwich structure having an elastomer film, 
         FIG. 14  shows an illustration of a sandwich structure having a display and a drive, and 
         FIG. 15  shows integration of a printed circuit board in a cabin component. 
     
    
    
     DETAILED DESCRIPTION OF EXEMPLARY EMBODIMENTS 
       FIG. 1  shows a schematic illustration of optical signal transmission according to the invention with a transmitter  101  and a receiver  103 , and a signal path  102  between the transmitter  101  and the receiver  103 . The transmitter  101  and the receiver  103  may in this case be arranged on different cabin components  104 ,  105 . The provision of an optical signal path  102  makes it possible to cover even relatively long spatial distances, and to flexibly cover distances between cabin components  104 ,  105  which are fitted with transmitters  101  and receivers  103 . 
       FIG. 2  shows an alternative embodiment for covering a distance between two cabin components  203 ,  204  by means of two elements  201 ,  202  which can be provided for inductive power transmission. 
     The arrangements shown in  FIG. 1  and  FIG. 2  make it possible to react flexibly to situations which occur while cabin components are being fitted within an aircraft. This flexibility is particularly advantageous when having to bridge intermediate spaces which can occur only late on during the assembly process. 
       FIG. 3  shows a longitudinal section through a cabin component  303  to which a carbon or glass tape  301 ,  302  can be applied. Optical or electrical paths can be positioned by application. 
       FIG. 4  shows a cross-sectional illustration of a cabin component  402 , in which the carbon or the glass tape  401  may be arranged on the cabin component  402 . 
       FIG. 5  shows an electrical conductor track  501  printed onto a cabin component  504  with a nozzle  502 , which can be moved in the direction  503 . 
       FIG. 6  show a cross section through a cabin component  602  having an electrical conductor track  601 , which can be applied by a nozzle to the cabin component  602 . 
     In the case of the methods shown in  FIG. 3  to  FIG. 6 , there is advantageously no need to prefabricate electrical or optical conductor tracks, thus allowing simpler work preparation for fitting the cabin components within an aircraft. This makes it possible to react flexibly to short-term changes in the arrangement of cabin components, which can represent the supports for the electrical conductor tracks and/or the optical signal paths. 
       FIG. 7  shows an optical waveguide  701 , which can be pressed into a cabin component  702 . On the one hand, this would advantageously allow the optical waveguide  701  to be protected against environmental influences without any need, for example, for a housing for this purpose. In addition, pressing the optical waveguide  701  into the cabin component  702  according to the invention results in a simplification of the assembly process since an appropriate optical waveguide would have also been fitted simply by the fitting of the cabin component. 
       FIG. 8  shows a plug connector  801  which has been pressed into a cabin component  802 , thus providing protection against damage, for example by mechanical loading for the plug connector  801 , without any additional components as well. Furthermore, the assembly process can be carried out more easily since the plug connector  801  associated with the cabin component  802  has already been fitted, and there is therefore no need for the plug connector  801  to be separately fitted. 
       FIG. 9  shows cabin components  902 ,  906 , in which a plug connector  903  can be embedded in one cabin component  902 , and a complementary plug element can be integrated in another cabin component  906 . Furthermore, according to the invention, components for forming a daisy-chain network can be integrated in the cabin components  902 ,  906 . The plug connectors  903  may connect electrical conductor tracks  905 ,  907  thus allowing electrical components to be driven, for example, by a drive board  901  via a plurality of cabin components  902 ,  906 . 
       FIG. 10  shows a sandwich structure according to the invention having a first prepreg layer  1001 , a first honeycomb  1002 , a board  1003 , comprising a printed circuit board on which electronic components can be arranged, a second honeycomb  1004  and a second prepreg layer  1005 . According to the invention, the sandwich structure can be connected by heating and pressing, in order to produce a finished cabin component which already has the appropriate electronics. This allows a prefabricated cabin component to be produced whose fitting can itself lead to the arrangement of the appropriate electronics, thus making it possible to speed up the assembly process, since there is no need to separately fit the electronics. Furthermore, in particular, the first honeycomb  1002  and the second honeycomb  1004  represent protection for the electronics against, for example, mechanical and/or thermal loading. 
     A prepreg (pre-impregnated fibres) means a semi-finished product which consists of endless fibres and a reactive resin. Prepregs are cured under pressure and a high temperature. During heating, the resin is liquefied and embeds the fibres before it starts to cure. Honeycombs which are arranged between two prepreg layers are used primarily for mechanical stiffening and, according to the invention, for protection of embedded electronics against, for example, mechanical loading. 
       FIG. 11  shows a cross section through a cabin component  1101  which has been pressed together and has a printed circuit board  1102 , which has been pressed in the centre of the cabin component and, for example, may have an external interface  1103 . 
       FIG. 12  shows a printed circuit board  1203  which can be arranged pressed in between two honeycombs  1201 ,  1205 , in which case the printed circuit board  1203  can be incorporated within a housing  1204  before the hot-pressing process, in order to be protected against mechanical and thermal loading. The internal area  1202  of the housing  1204  should be sufficiently large to allow sufficient space for the internal printed circuit board  1203 , even after the hot-pressing process. 
       FIG. 13  shows an embodiment according to the invention of an internal area  1303  for holding, for example, a printed circuit board, in which case an elastomer film for vibration damping can be arranged between the individual honeycombs  1301 ,  1304 . This makes it possible to provide twisting protection for a printed circuit board which is located within the internal area  1303 . 
       FIG. 14  shows an arrangement of a display  1403  having electronics  1401  which drive the display  1403 , in which case the electronics  1401  can be pressed into the honeycomb  1402 , thus making it possible to protect the electronics  1401  against mechanical loading. Electrical conductor tracks  1404  or optical signal paths can be passed through the honeycomb  1402  between the electronics  1401  and the display  1403 , in order to allow the display  1403  to be driven. 
       FIG. 15  shows a printed circuit board  1502  on which electronic components can be arranged, for example resistors, diodes, integrated circuits, etc. This printed circuit board  1502  can be introduced in a recess  1503  in a cabin component  1506 . The embedded printed circuit board  1502  can be sealed by a cover  1501 , in order to allow protection against mechanical loading and/or for example liquids. By way of example, conductor tracks  1504  may have already been arranged in the cabin component  1506 , in order to allow a connection to other printed circuit boards  1505 , sensors and/or actuators. 
     It should be noted that the term “comprise” does not exclude further elements or method steps and, in the same way, the term “one” or “a” does not preclude a plurality of elements and steps. 
     The reference symbols used serve only to improve understanding and should in no way be considered restrictive, with the scope of protection of the invention being reflected by the claims. 
     LIST OF REFERENCE SYMBOLS 
     
         
           101  Transmitter 
           102  Optical signal path 
           103  Receiver 
           104  Cabin component 
           105  Cabin component 
           201  Component for inductive power transmission 
           202  Component for inductive power transmission 
           203  Cabin component 
           204  Cabin component 
           301  Carbon or glass tape 
           302  Roll of carbon or glass tape 
           303  Cabin component 
           401  Optical or electrical path 
           402  Cabin component 
           501  Electrical conductor track 
           502  Nozzle 
           503  Movement direction 
           504  Cabin component 
           601  Conductor track 
           602  Cabin component 
           701  Optical waveguide 
           702  Cabin component 
           801  Plug connector 
           802  Cabin component 
           901  Component 
           902  Cabin component 
           903  Plug connector 
           904  Electrical conductor track 
           905  Electrical conductor track 
           906  Cabin component 
           907  Electrical conductor track 
           1001  Prepreg layer 
           1002  Honeycomb 
           1003  Printed circuit board 
           1004  Honeycomb 
           1005  Prepreg layer 
           1101  Cabin component 
           1102  Printed circuit board 
           1103  External interface 
           1201  Honeycomb 
           1202  Recess 
           1203  Printed circuit board 
           1204  Housing 
           1205  Honeycomb 
           1301  Honeycomb 
           1302  Elastomer film 
           1303  Recess 
           1304  Honeycomb 
           1401  Printed circuit board 
           1402  Honeycomb 
           1403  Display 
           1404  Electrical conductor track 
           1405  Prepreg layer 
           1406  Prepreg layer 
           1501  Cover 
           1502  Printed circuit board 
           1503  Recess 
           1504  Electrical conductor track 
           1505  Component 
           1506  Cabin component