• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:

    公开号:FR3017598A1
    申请号:FR1551136
    申请日:2015-02-12
    公开日:2015-08-21
    发明作者:Norbert Staudigel
    申请人:Diehl Aircabin GmbH；
    IPC主号:
    专利说明:

    [0001] DESCRIPTION The invention relates to an aircraft or aircraft panel for an interior space of an aircraft or aircraft and a method of manufacturing the aircraft or aircraft panel. The aircraft or aircraft panel has a sandwich structure that includes a center section and a cover section as sandwich layers. Aircraft or aircraft panels are used in aircraft for example for the coating of side walls, floors and / or ceilings of the aircraft. They can also be made in the form of a constituent element of an interior of the aircraft, for example an upper storage compartment. Such an upper storage compartment, in which passengers can store objects and luggage, is most often placed above the passenger seats of the aircraft. A storage module for an interior space of an aircraft or aircraft is described for example in the publication of application DE 10 2007 030 331 A1. The storage module comprises at least one receptacle and at least one housing for receiving the receptacle. at least one passenger service delivery channel being integrated into the housing. This channel is designed as a retainer for adjacent components such as cables, tubes, pipes, PSC components, light sources, etc. The receptacle and / or the housing is formed of plastic sandwich panels reinforced with carbon fibers. The object of the invention is to provide an aircraft or aircraft panel which is improved from a functional point of view and simple to manufacture.
    [0002] This object is achieved by an aircraft panel for an interior space of an aircraft or aircraft, which aircraft panel has a sandwich structure which comprises a central section and a covering section as sandwich layers, the covering section comprising a layer of prepreg, and which aircraft panel comprises at least one switching element for activating at least one electrical equipment of the aircraft or the aircraft, said at least one element of switching being fixed in the cover section by the prepreg layer, and which aircraft panel comprises at least one support member for supporting and holding the switching element in the aircraft panel, the support member being formed as a wafer having a central depression and a peripheral edge region. The panel according to the invention may, in addition, have one or more of the following additional features: the prepreg layer is located at a distance from the central section and disposed in the direction of a visible face of the panel; aircraft, said at least one switching element being arranged in a succession of layers at least in certain areas under the prepreg layer; the panel has a lower layer of prepreg which is in contact with and / or rests on the central section, said at least one switching element being arranged in the succession of layers between the prepreg layer and the lower layer of prepreg; said at least one switching element is fixed indirectly or directly in the covering section by the prepreg layer. the panel has at least one connection line which is electroconductively connected to said at least one switching element, said at least one connecting line being covered by the prepreg layer and / or embedded therein. the support element rests on the central section and / or is depressed at least partly in the central section in such a way that the support element is in particular made and can be connected to the central section in such a way, that the switching element is integrated equiplanarly in the aircraft panel. the switching element rests on the edge region of said at least one support element and can be depressed, at least at its center, in the central depression of said at least one support element, the switching element being realized so that it is possible to actuate the switching element by depression in the central depression and thus activate the electrical equipment. said at least one switching element has a maximum height of less than 1 millimeter, preferably less than 0.7 millimeter. The prepreg layer has at least one housing for said at least one switching element and said at least one support element, said at least one support element and said at least one switching element being placed in the housing, said at least one switching element being covered at least in certain areas by at least one layer of the succession of layers. the covering section comprises an upper sheet, which upper sheet extends between the at least one switching element and the prepreg layer, the at least one switching element being connected by bonding material to the pre-impregnated layer; impregnated by the upper sheet and indirectly fixed by it in the covering section. the covering section comprises a lower sheet, which bottom sheet extends between said at least one support member and said at least one switching element, said at least one switching element being connected by material connection to said at least one support element by the lower sheet. the panel has a cover sheet for the insulation and / or protection against touching of said at least one switching element, the covering sheet being arranged on one or on the visible face of the aircraft panel and / or forming this one. - The central section comprises a honeycomb core and / or is formed by it. the panel comprises a base section which has another layer of prepreg or is formed by it. The subject of the invention is also a method for manufacturing an aforementioned aircraft panel, characterized by the steps of placing said at least one switching element in the indirect or direct cover and fixing section of said at least one switching element in the cover section by the prepreg layer. Thus, in the context of the invention, there is provided an aircraft panel for an interior space of an aircraft, in particular for an aircraft cabin. The aircraft panel is preferably made at least partly and / or in certain areas in the form of a trim element or aircraft equipment. For example, the aircraft panel may dress faces inside the aircraft. In this function, it can be made in the form of a floor covering, ceiling and / or wall of the interior space of the aircraft Alternatively or optionally, the aircraft panel can make part of an interior arrangement of the aircraft. In particular, the aircraft panel can be made in the form of a seat cover or a side wall of an upper storage compartment, in particular of what is called a "pivot bin", of Aircraft The aircraft panel has a sandwich structure that includes a central section and a cover section as sandwich layers. The covering section preferably has a visible face of the aircraft panel, which, when integrated into the interior space of the aircraft, can be seen and touched by the passengers. Preferably, the covering section covers the central section and / or is disposed above the central section. Optionally, the sandwich structure comprises a base section as an additional sandwich layer. In particular, the central section is disposed between the cover section and the base section. The covering section comprises a prepreg layer. Optionally, the prepreg layer is made in the form of a fiber composite material. Preferably, the prepreg layer is in the form of a semi-finished product composed of continuous fibers and an uncured thermosetting plastic matrix. Carbon fibers are preferably used as continuous fibers, or alternatively, for example, glass fibers, basalt fibers or aramid fibers. The aircraft panel comprises at least one switching element, in particular electrical, which is designed to activate at least one electrical equipment of the aircraft, such as an electrical consumer. For example, the electrical equipment can be made in the form of a switch for activating a blind of the aircraft, in particular a window shutter, and / or a switch for activating a parking mechanism. opening the upper storage compartment, in particular what is called an "automated bin", and / or switching lighting equipment, in particular a reading light, etc. Alternatively or optionally, the electrical equipment may be in the form of a control switch, a service button and / or a lighting switch of the aircraft. Preferably, the switching element has a switching surface whose mechanical actuation triggers a switching and thus activates the electrical equipment. Said at least one switching element is fixed in the covering section by the prepreg layer. In particular, the prepreg layer forms a fixing layer for the switching element. In particular, said at least one switching element can be arranged in a succession of layers under the prepreg layer, said at least one switching element being able to be covered at least in certain zones by at least one layer of the succession of In particular, the switching element can, in top view, be covered at least in part by the prepreg layer and / or be at least partly covered by the layer of prepreg. by one or more layers of the succession of layers which can / can be covered at least in part by the prepreg layer. In particular, said at least one switching element can be integrated and / or recessed at least in certain areas in the covering section. The attachment, in particular the integration and / or the embedding, of the switching element is preferably carried out during manufacture, in particular during a pressing or a pressing operation of the sandwich layers to form the sandwich structure. In a preferred manner, the aircraft panel is manufactured so that it is no longer necessary to mount the at least one switching element thereafter on the finished aircraft panel, already pressed. Preferably, the switching surface of the switching element is disposed on the visible face of the aircraft panel and / or the switching surface forms part of the visible face. In particular, the switching surface is arranged on the visible side so that it can be seen and touched. Passengers and / or flight crew can thus simply operate the switching element to activate the electrical equipment. It is advantageous that the integration of said at least one switching element during the manufacture of the aircraft panel, in particular during the pressing of the sandwich structure, makes unnecessary manufacturing steps otherwise necessary, such as milling a housing. for the switching element, placing the switching element in the housing and fixing the switching element in the housing. This saves work time and the corresponding costs. It is furthermore advantageous that the attachment of the switching element in the cover section by the prepreg layer renders a housing for the switching element superfluous. This helps reduce weight and save material. It is furthermore advantageous if the switching element fixed in the covering section is fully functional and at the same time has positive haptic and optical properties.
    [0003] The aircraft panel also includes at least one support member for the at least one switching element, the support member being adapted to support or receive the switching element by supporting it. For example, the support member may be formed of a prepreg of phenolic resin, for example bilayer, cured. In particular, said at least one support element can be made in the form of a plate of material called Airlam. Preferably, said at least one support element is made in the form of a support and / or a support for said at least one switching element. Said at least one switching element may preferably be arranged above the support element. In particular, it rests at least in part and / or in certain areas on the support element. For example, said at least one support member has the contour and / or the shape of a wafer having a central depression, in particular a central countersink. An edge zone, in particular a peripheral zone, of the wafer may extend around the central depression, projecting with respect to the depression. In a particularly preferred manner, said at least one switching element rests on the edge zone, in particular protruding with respect to the depression, and / or is supported on it when it is fixed in the covering section by the prepreg layer, in particular so that the region of the switching element which does not rest is located at a distance from the bottom of the depression. Because the switching element rests on the edge area, it can be depressed into the central depression of the wafer and actuated. In particular, the switching element can be actuated by exerting a pressing force on the switching element in the region of the depression, so that an actuation of the switching element can in particular be caused by a depression. a switching surface of the switching element towards the central depression, resulting in the activation or deactivation of the electrical equipment of the aircraft. The arrangement of the supporting and / or supporting support member with a void or free space formed by the depression under the switching element allows the switching element to be erased towards the central depression when pressing the sandwich structure during manufacture (curing). This advantageously avoids deterioration of the switching element when fastened in the cover section by the prepreg layer. In a preferred embodiment of the invention, the prepreg layer is located at a distance from the central section and disposed in the direction of the visible face of the aircraft panel. Preferably, said at least one switching element is disposed in a succession of at least 15 layers in certain areas under the prepreg layer. In particular, the prepreg layer forms a fixing layer for the at least one switching element. In a possible embodiment of the invention, the aircraft panel comprises a lower layer of prepreg. Optionally, the lower layer of prepreg is in contact with and / or rests on the center section. In particular, the lower layer of prepreg is designed to connect the top layer to the core layer. Preferably, the lower layer of prepreg is disposed in the succession of layers between the prepreg layer and the central section. Said at least one switching element is preferably arranged in the succession of layers between the prepreg layer and the lower prepreg layer. Particularly preferably, the prepreg layer affixes said at least one switching element in the cover section indirectly or directly. It is possible, in the context of the invention, for the direct attachment, the switching element is covered at least in part and / or in certain areas by the prepreg layer. It is nevertheless particularly preferred that the switching element is connected to the prepreg layer via another layer of the layer succession, in particular via another fold and / or of another sheet, especially by an adhesive sheet, and thus indirectly attached thereto in the cover section. In a particularly preferred manner, the switching element is covered by the other fold and / or the other sheet and the other fold and / or the other sheet is covered by the prepreg layer.
    [0004] A preferred embodiment of the invention provides that the aircraft panel comprises at least one connection line for connecting and / or connecting said at least one switching element to a voltage source. For example, said at least one connecting line is made in the form of a conductive track, in particular a copper foil. Preferably, said at least one connecting line is covered by the prepreg layer and thus fixed in the covering section. In particular, said at least one connecting line extends under the prepreg layer. It is also possible that it is placed on or above the lower layer of prepreg. In particular, said at least one connecting line extends between the lower layer of prepreg and the prepreg layer. In particular, said at least one connection line is put in place during the manufacture of the aircraft panel and then covered by the prepreg layer. For example, said at least one connecting line extends parallel to the covering section of the aircraft panel. Therefore, said at least one connecting line and the switching element attached thereto are reliably integrated. in the overlap section. Preferably, said at least one connection line is electrically conductive, for example brazed, to said at least one switching device to form a switching unit. Particularly preferably, the connection line is electroconductively connected to the switching element to form a switching unit already prior to pressing the sandwich structure. Preferably, the switching unit is placed on the lower layer of prepreg and / or disposed above it before pressing the sandwich structure. In particular, the lower prepreg layer, the switching unit and the prepreg layer are pressed together in the cover section or to form the cover section. In a preferred embodiment of the invention, said at least one switching element is formed of a metal alloy. The switching element may have a diameter in the range of up to 8 mm or 12 mm, or even 15 mm. In particular in this embodiment, it is particularly advantageous that the switching element is of relatively flat construction. The switching element may preferably have a height of up to 1 millimeter or a height of up to 0.7 millimeter. Such dimensions make it possible to achieve a space-saving fixing which can be carried out in particular by a layer of prepreg in the covering section. In particular, such a prepreg layer makes it possible to achieve a relatively flat integration in the covering section. For example, said at least one switching element may be in the form of at least one "T switch" switch from Nicomatic. In a preferred embodiment of the invention, at least one housing for said at least one switching element is formed in the prepreg layer. The housing is for example made in the form of a recess in the prepreg layer, which has a shape and size corresponding to those of the switching element and / or is adapted thereto. Preferably, said at least one switching element and, optionally, also said at least one support element, are put in place in the housing. In particular, said at least one support element is placed in the housing first, said at least one switching element being placed in particular on the edge region of the support element so as to rest on the in the housing. A preferred embodiment of the invention provides that the cover section comprises an upper sheet and / or a lower sheet. Preferably, the lower sheet is disposed between the support member and the switching member. The support element and the switching element may be connected together, preferably by material connection, in particular during manufacture of the aircraft panel, via the lower sheet. The lower sheet is preferably in the form of a lower adhesive sheet. For example, the lower adhesive sheet is made in the form of an adhesive film or tape. The support element and the switching element can thus be glued together, in particular during the manufacture of the aircraft panel. In a particularly preferred manner, the topsheet rests on the switching element and extends beyond this one. Preferably, the topsheet forms the other layer of the succession of layers through which said at least one switching element is connected to the prepreg layer, preferably by material bonding. Preferably, the topsheet extends over one or the switching surface of the switching element. In particular, the topsheet is disposed between the prepreg layer and the switching element. Preferably, the topsheet and the prepreg layer overlap in a top view. The topsheet is preferably in the form of an upper adhesive sheet. For example, the upper adhesive sheet is made in the form of an adhesive film or adhesive tape. The switching element can thus be bonded with the prepreg layer, in particular during the manufacture of the adhesive panel. 'aircraft. This allows in particular the indirect fixing of said at least one switching element in the covering section by the prepreg layer. A preferred constructive embodiment of the invention provides for the aircraft panel to include a cover sheet. Preferably, the visible face comprises the cover sheet and / or the visible face is formed by the cover sheet. For example, the cover sheet is made in the form of a polyvinyl fluoride sheet. In particular, the polyvinyl fluoride sheet is in the form of a transparent sheet, especially in the form of a tedlar sheet. Preferably, the cover sheet extends over the prepreg layer and at the same time onto the switching surface of the switching element attached in the cover section. In particular, the cover sheet forms a surface of the aircraft panel, for example in the form of a decorative and / or protective sheet. Optionally, the cover sheet serves as insulation and / or protection against touch for said at least one switching element and for the connection line connecting thereto. This makes it possible to advantageously guarantee safe operation of said at least one switching element in the aircraft panel. Optionally, it is also possible to provide on the cover sheet an additional layer of paint which forms the surface and / or the visible face of the aircraft panel The paint layer makes it possible in particular to improve the appearance and / or the touch of the aircraft panel and increase its mechanical strength. In a preferred embodiment of the invention, the central section of the aircraft panel is formed by a honeycomb core and / or the central section comprises the honeycomb core. For example, the honeycomb core is formed of a paper-like material and / or cardboard. In particular, a coated aramid paper is used for the honeycomb core. This has advantages in particular from the point of view of weight reduction of the aircraft panel. The optional base section is formed of, for example, another layer of prepreg and / or includes it. Another possible object of the invention relates to a method of manufacturing the aircraft panel as described above, which consists, in one step, of setting up said at least one switching element in the covering section and, in a subsequent step, to fix said at least one switching element indirectly or directly in the cover section by the prepreg layer. Other features, advantages and effects of the invention result from the following description of preferred embodiments of the invention. FIG. 1 is a cross-section of a principal structure of an aircraft panel comprising a cover section, a center section and a base section, with a switching element fixed in the cover section; Figure 2 is a top view of the switching element of Figure 1; Figure 3 is a cross section of the switching element of Figure 1; FIG. 4 is a top view of a visible face of the aircraft panel of FIG. 1 with the switching element fixed in the covering section; Figure 5 is a schematic flow diagram of a manufacturing process of the aircraft panel of Figure 1. Corresponding or identical parts are designated by the same references in the figures. FIG. 1 shows a cross-section of an example of an aircraft panel 1 for an interior space of an aircraft, on which a section line extends parallel to a longitudinal extension of the aircraft panel 1. The aircraft panel 1 is made in the form of a trim element used to dress the interior space and / or a piece of equipment used to equip an interior. The aircraft panel 1 has a sandwich structure 2 which comprises, as sandwich layers, a covering section 3, a central section 4 and a base section 5. The central section 4 is arranged between the covering section 3 and the base section 5. During the manufacture of the aircraft panel 1, the base section 5, the central section 4 and the covering section 3 are laid one on the other and pressed together to form the structure. sandwich 2. The covering section 3 comprises a prepreg layer 6 and a lower prepreg layer 7 which are made in the form of a fiber composite material. The base section 5 is formed of a fiber composite material, in particular another prepreg layer 11. Each of the prepreg layers 6; 7; It is in the form of a semi-finished product composed of continuous fibers and an uncured thermosetting plastic matrix. The central section 4 has a honeycomb core comprising a plurality of cells formed of a material of the paper or cardboard type. The lower layer of prepreg 7 rests on the central section 4 and connects the cover section 3 to the central section 4. The prepreg layer 6 is disposed at a distance from the central section 4 in the direction of a face visible from the aircraft panel 1. When the aircraft panel 1 is integrated into the aircraft as a trim element or equipment item, the visible side 10 can be seen and touched by the passengers.
    [0005] The prepreg layer 6 has a housing 14 for a switching element 8 of the aircraft panel 1 which is fixed in the covering section 3. The housing 14 is in the form of a recess whose shape and / or or the size correspond to those of the switching element and / or are adapted thereto. In particular, the switching element 8 is arranged in a succession of layers at least in certain areas under the prepreg layer 6. The housing 14 may also be designed in shape or size so as to overlap the switching element 8 in plan view. The switching element 8 is shown in a top view in FIG. 2 and in cross-section in FIG. 3. The switching element 8 can be actuated by exerting pressure on a switching surface 18. The actuation the switching element 8 makes it possible to activate an electrical equipment of the aircraft. For example, the electrical equipment can be made in the form of a switch for activating a blind of the aircraft, in particular a shutter. and / or a switch for activating an opening mechanism of the upper storage compartment, in particular what is called an "automated bin". In a variant, the electrical equipment may be designed as a control switch, a service button and / or a lighting switch of the aircraft. The switching element 8 is made by example in the form of a switch "T switch" of the Nicomatic company. It has a circular outer contour with two contacts 12; 13 protruding laterally for the connection of at least one connecting line 17 (Figure 1). The switching element 8 may be formed of a metal alloy and has a diameter D of 8 to 15 millimeters at most, in particular 8 to 10 millimeters, a relatively low height H relative to other solutions, namely 1 millimeter at most, preferably 0.7 millimeter at most. In particular, the mentioned external dimensions of the switching element allow for its small space-saving integration into the covering section 3 of the aircraft panel 1 (see Figs 1 and 4). The aircraft panel 1 has at least one electrical connection line 17 (FIG 1) for the connection of the switching element 8 to a voltage source of the aircraft. This is carried out in the form of a conductive track made of copper wire and electroconductively connected to the contacts 12; 13 of the switching element 8, for example brazed to the contacts 12; 13. The connecting line 17 extends under the prepreg layer 6 and parallel or substantially parallel to the central section 4.
    [0006] As shown in FIG. 1, the aircraft panel 1, in particular the covering section 3, comprises a support element 9 for the switching element 8. The support element 9 is arranged in the housing 14 on the lower prepreg layer 7. It is designed to receive and / or support the switching element 8. The support element 9 is formed of a phenolic resin prepreg, for example bilayer, hardened (plate of Airlam material). It is in the form of a wafer having a central depression 15 and a peripheral edge area 16. The switching element 8 rests by its edges and / or by the contacts 12; 13 in the edge region 16 of the support member 9. In particular, the diameters of the support member 9 and the switching element 8 are tuned and / or matched to each other. The switching surface 18 (FIGS 2 and 3) of the switching element 8 is arranged above the depression 15. The switching element 8 can thus be depressed without resistance in the central depression 15 and thus actuated, so that the electrical equipment is activated. In addition, the aircraft panel 1 can be pressed without problems, without damaging the switching element 8 since it can fade into the central depression 15 during pressing, to assemble the various sections 3; 4; And forming the sandwich structure 2. The covering section 3 comprises a lower sheet which is in the form of a lower adhesive sheet 19. The lower adhesive sheet 19 is disposed between the support member 9 and the element 8. It connects together the support element 9 and the switching element 8 by bonding material, in particular the support element 9 and the switching element 8 are glued together by the lower adhesive sheet 19. The switching element 8 with the connecting line 17 connected thereto is arranged at least in certain areas under the prepreg layer 6. For the indirect fixing of the switching element 8 in the covering section 3 by the prepreg 6, the covering section 3 has an upper sheet which is in the form of an upper adhesive sheet 20. The upper adhesive sheet 20 covers the switching 8 and / or extends entirely on it. It is arranged in the succession of layers between the switching element 8 and the prepreg layer 6, being covered at least in part and / or in certain areas by the prepreg layer 6 and / or overlapping this one in view from above. The switching element 8 is connected by bonding of material, in particular bonded to the prepreg layer 6 by the upper adhesive sheet 20. The switching element 8 is thus fixed indirectly in the covering section 3 by the prepreg layer 6. The aircraft panel 1 has a cover sheet 21, in particular a sheet of polyvinyl fluoride (tedlar sheet), which is arranged on the prepreg layer 6 and forms the visible face 10 of the aircraft panel 1. The cover sheet 21 is designed for the insulation and / or the touch protection of the switching element 8. Optionally, a layer of paint can be applied to the sheet 21 to improve the appearance and to protect the surface of the aircraft panel 1. FIG. 4 shows a view from above of the visible face 10 of the aircraft panel 1. The switching surface 18 of the switching element 8 fixed in the 3 by the prepreg layer 6 can be seen and operated by the passengers and / or the cabin crew. The visible face 10 is formed by the cover sheet 21. The cover sheet 21 extends entirely over the prepreg layer 6 and the switching surface 18 of the aircraft panel 1. As an option, a layer of Additional paint may be applied to the cover sheet 21. FIG. 5 shows a schematic flow diagram of a method of manufacturing the aircraft panel 1. The method comprises the following steps: 22: placement of said at least one element of switching 8 in the cover section 3; 23: indirect or direct attachment of said at least one switching element 8 in the covering section 3 by the prepreg layer 6. The parts, elements, objects and details of the invention are referenced as follows in the appended figures. : 1: aircraft panel 2: sandwich structure 3: cover section 4: central section 35 5: base section 6: prepreg layer 7: lower prepreg layer - 16- 8: switching element 9: support element 10: visible face 11: other prepreg layer 12: first contact 13: second contact 14: housing 15: central depression 16: edge zone 17: connection line 18: switching surface 19: sheet lower adhesive 20: upper adhesive sheet 21: cover sheet 22: first process step 23: second process step D: diameter H: height Of course, the invention is not limited to the embodiment of the invention. laughed and represented in the accompanying drawings. Modifications are possible, particularly from the point of view of the constitution of the various elements or by substitution of technical equivalents, without departing from the scope of protection of the invention.
    权利要求:
    Claims (15)
    [0001]
    REVENDICATIONS1. Aircraft panel (1) for an interior space of an aircraft or aircraft, which aircraft panel (1) has a sandwich structure (2) which comprises a central section (4) and a cover section ( 3) as sandwich layers, the covering section (3) comprising a prepreg layer (6), and which aircraft panel (1) comprises at least one switching element (8) for activate at least one electrical equipment of the aircraft or aircraft, said at least one switching element (8) being fixed in the covering section (3) by the prepreg layer (6), and which panel 10 of aircraft (1) comprises at least one support element (9) for supporting and holding the switching element (8) in the aircraft panel (1), the support element (9) being made under the shape of a wafer having a central depression (15) and a peripheral edge region (16). 15
    [0002]
    Aircraft panel (1) according to claim 1, characterized in that the prepreg layer (6) is located at a distance from the central section (4) and arranged in the direction of a visible face (10). ) of the aircraft panel (1), said at least one switching element (8) being arranged in a succession of layers at least in certain areas under the prepreg layer (6).
    [0003]
    3. aircraft panel (1) according to claim 2, characterized in that it has a lower layer of prepreg (7) which is in contact with the central section (4) and / or rests on it said at least one switching element (8) being disposed in the succession of layers 25 between the prepreg layer (6) and the lower prepreg layer (7).
    [0004]
    Aircraft panel (1) according to one of claims 1 to 3, characterized in that said at least one switching element (8) is fixed indirectly or directly in the covering section (3) by the Prepreg layer (6).
    [0005]
    5. Aircraft panel (1) according to one of claims 1 to 4, characterized in that it has at least one connecting line (17) which is electroconductively connected to said at least one element 18- switching (8), said at least one connecting line (17) being covered by and / or embedded in the prepreg layer (6).
    [0006]
    6. Aircraft panel (1) according to one of claims 1 to 5, characterized in that the support element (9) rests on the central section (4) and / or is depressed at least partly in the central section (4) in such a way that the supporting element (9) is in particular made and connectable to the central section in such a way that the switching element (8) is integrated equiplanally in the panel aircraft (1).
    [0007]
    Aircraft panel (1) according to claim 6, characterized in that the switching element (8) rests on the edge region (16) of said at least one support element (9) and can be depressed, at least at its center, in the central depression (15) of said at least one support element (9), the switching element (8) can be made so that it is possible to actuate the switching element (8) by depression in the central depression (15) and thereby activate the electrical equipment.
    [0008]
    8. aircraft panel (1) according to one of claims 1 to 7, characterized in that said at least one switching element (8) has a maximum height of less than 1 millimeter, preferably less than 0.7 millimeter.
    [0009]
    9. Aircraft panel (1) according to one of claims 6 to 8, characterized in that the prepreg layer (6) has at least one housing (14) for said at least one switching element (8). ) and said at least one support element (9), said at least one support element (9) and said at least one switching element (8) being put into place in the housing (14), said at least one switching element (8) being covered at least in certain areas by at least one layer of the succession of layers.
    [0010]
    10. Aircraft panel (1) according to one of claims 1 to 9, characterized in that the covering section (3) comprises a top sheet (20), which top sheet (20) extends between said at least one switching element (8) and the prepreg layer (6), said at least one switching element (8) being connected by bonding material to the prepreg layer (6) by the topsheet (20) and indirectly secured thereto in the cover section (3).
    [0011]
    Aircraft panel (1) according to one of claims 6 to 10, characterized in that the covering section (3) comprises a lower sheet (19), which bottom sheet (19) extends between said at least one support element (9) and said at least one switching element (8), said at least one switching element (8) being connected by material connection to said at least one support element (9) by the lower sheet (19).
    [0012]
    12. Aircraft panel (1) according to one of claims 1 to 11, characterized in that it has a cover sheet (21) for the insulation and / or protection against the touch of said at least one element switching member (8), the cover sheet (21) being disposed on or on the face (10) of the aircraft panel (1) and / or forming thereof.
    [0013]
    13. Aircraft panel (1) according to one of claims 1 to 12, characterized in that the central section (4) comprises a honeycomb core and / or is formed by it.
    [0014]
    14. Aircraft panel (1) according to one of claims 1 to 13, characterized in that it comprises a base section (5) which has another layer of prepreg (11) or is formed by it.
    [0015]
    15. A method of manufacturing the aircraft panel (1) according to one of claims 1 to 14, characterized by the following steps: - 22: implementation of said at least one switching element 20 (8) in the section of covering (3) - 23: indirect or direct fixing of said at least one switching element (8) in the covering section (3) by the prepreg layer (6).
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    同族专利:
    公开号 | 公开日
    FR3017598B1|2019-04-26|
    BR102015003054A2|2015-12-15|
    DE102014002365A1|2015-08-20|
    US20150232165A1|2015-08-20|
    CA2880851A1|2015-08-18|
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    法律状态:
    2016-02-18| PLFP| Fee payment|Year of fee payment: 2 |
    2017-02-17| PLFP| Fee payment|Year of fee payment: 3 |
    2018-02-23| PLFP| Fee payment|Year of fee payment: 4 |
    2018-11-02| PLSC| Publication of the preliminary search report|Effective date: 20181102 |
    2018-11-16| CD| Change of name or company name|Owner name: DIEHL AVIATION LAUPHEIM GMBH, DE Effective date: 20181016 |
    2020-02-19| PLFP| Fee payment|Year of fee payment: 6 |
    2021-11-12| ST| Notification of lapse|Effective date: 20211005 |
    优先权:
    申请号 | 申请日 | 专利标题
    DE102014002365.6|2014-02-18|
    DE102014002365.6A|DE102014002365A1|2014-02-18|2014-02-18|Aircraft panel for an interior of an aircraft and method for manufacturing the aircraft panel|
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