• 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:
    Interior trim part (2, 3, 4, 5, 6) for an aircraft cell with a support structure, wherein at least one support position (9) is provided on the interior side, which is designed for load suspension and precast assembly (1) for an aircraft cell with attachable to the aircraft cell Interior trim parts (2, 3, 4, 5, 6), wherein the interior trim parts (2, 3, 4, 5, 6) have a support structure and inside space at least one support position (9), which is designed for load-bearing, and that the interior trim parts (2, 3, 4, 5, 6) connecting points (15), where they are mutually positively connected.
    公开号:AT515159A1
    申请号:T899/2013
    申请日:2013-11-20
    公开日:2015-06-15
    发明作者:Martin Weger；Wolfgang Burger
    申请人:Helikopter Air Transp Gmbh；
    IPC主号:
    专利说明:

    The invention relates to an interior trim part and a finished part assembly for an aircraft cell with interior trim parts attachable to the airframe.
    In aircraft construction, it is necessary for various reasons to provide an interior trim inside the aircraft cell. Especially in ambulance aircraft or rescue helicopters, there is the additional requirement of a hygienic and externally protected environment for transporting patients.
    The hitherto customary interior trim panels serve essentially only to form a closed smooth surface as the termination of the aircraft interior and are not designed for the suspension of larger loads. In the case of an ambulance or rescue helicopter, various items of equipment, such as e.g. For the resuscitation and stabilization of patients, measuring and supply devices should be hung on the sides, for which a separate load-bearing construction with side walls, a top wall and a solid bottom plate must be provided, which is formed directly adjacent to the interior trim for reasons of space.
    In this way, the usable interior reduces and the weight of the aircraft increases.
    The object of the present invention is to provide an interior trim part and a prefabricated part assembly with which both a better space utilization and a lower weight load can be achieved.
    According to the invention, this is achieved in an interior trim part of the type mentioned at the outset in that it has a support structure, wherein at least one support position is provided on the interior space, which is designed for load-bearing.
    Thus, the interior trim panel of the present invention is adapted to be attached directly to the aircraft cell but at the same time reinforced to receive load forces, with predefined mounting positions provided at predetermined locations of the interior trim panels where the load forces can be introduced into the interior trim panels of the invention, e.g. in the form of parts reinforced for this purpose in which threads, hooks, eyes or similar attachment points are present.
    In this way can be dispensed with an additional support structure and saved according to space.
    Since the mounting positions are already built into the interior trim parts at the time of manufacture, no changes can be made to the position of the mounting positions after the interior trim parts are installed in an airframe, unless the interior trim part is replaced.
    However, in order to provide for a subsequent change in the mounting positions, in accordance with another embodiment of the invention, the underfacing interior trim members may comprise a plurality of selectable mounting positions in a grid-like arrangement, thereby providing variable mounting of, in particular, medical equipment.
    One possible form of implementation may be that the mounting positions are formed by concealed threaded inserts integrated in the interior trim parts, the threaded inserts for receiving
    Support devices are formed. The threaded inserts are only "activated". if they are needed. Unused threaded inserts can also be resealed to achieve a smooth surface.
    A further embodiment of the invention may consist in that the inner lining parts for increasing the rigidity in a manner known per se have reinforcements or ribs which may be formed at predeterminable locations.
    In order to achieve the above-mentioned objects of the invention, in the case of a prefabricated subassembly initially mentioned with two or more interior trim parts, it may be provided that the interior trim parts have connection points to which they can be frictionally connected to one another.
    In this way, a composite effect and thereby an increase in the load capacity is achieved.
    According to a further aspect of the invention, the inner lining parts may have holding brackets for connection to and for force introduction into the aircraft cell, whereby the loads acting on the inner lining parts can be derived via diagonal elements of the aircraft cell.
    In particular, the interior trim parts can be screwed to the aircraft cell via the retaining angles.
    According to a variant of the invention, the inner lining parts may comprise at least two side parts and a cover part, which are connectable to an U-shaped cross section. In this way a very effective union can be achieved.
    In a further embodiment of the invention, it may be provided that the interior trim parts below the surface have a plurality of selectable mounting positions in a grid-like arrangement to enable variable attachment of, in particular, medical equipment devices.
    According to another embodiment, parts of the standard interior trim panels can be replaced by supporting interior trim panels according to the invention, which in turn are designed to have at least one or more mounting positions for load bearing.
    Due to the high rigidity of the assembly of the invention achieved by the merger of the interior trim parts, a floor plate of low wall thickness which is not in frictional connection with the interior trim parts can be installed in the floor area of the aircraft compartment.
    According to a further embodiment of the invention, the bottom plate supports, e.g. B. for a stretcher, and provides a protection of the aircraft original floor ready.
    Furthermore, the invention relates to an aircraft with a prefabricated subassembly according to the invention mounted in the aircraft cell, wherein the aircraft is e.g. a helicopter, especially a rescue or
    Emergency helicopter, or may be an aircraft having the ability to integrate flexibly needed equipment into the cabin.
    The invention will be explained in detail with reference to the embodiment explained in the drawings. It shows
    Fig.l and 2 are perspective views of an embodiment of the invention assembled from the interior trim parts assembly of the invention;
    3 shows the component group according to Fig.l and 2 in one
    Exploded view;
    4 is a perspective view of a bottom plate;
    5 shows a section through a detail of a Innenverkleidungsteils according to Fig.l and
    Fig. 6 is a section through a junction between an interior trim panel of the invention and an aircraft compartment wall.
    3 shows interior trim parts 2, 3, 4, 5 a
    Prefabricated assembly in the uninstalled state, which for adaptation to the course of an aircraft cell by windows, entrances, etc. different shape with
    Wells, bulges, passages, etc., and are formed with a closed area. For example, apertures 90 are adapted to the windows of the respective airframe. The aircraft cell may be, for example, that of a rescue helicopter or other aircraft.
    The interior trim parts 2, 6 cover opposite side areas of the aircraft cell, not shown, while the interior trim parts 4, 5 are designed for the ceiling area. The interior trim part 3 is a cross member extending transversely to the longitudinal direction. The number and shape of the interior trim parts are not limited and may be adapted to the type and purpose of use of the aircraft.
    The interior trim parts 2, 3, 4, 5, 6 are thus given by way of example in FIGS. 1 to 3 and can be changed according to the design of the aircraft, so that the shape of the interior trim parts 2, 3, 4, 5, 6 is freely variable within the scope of the invention ,
    At the areas facing the aircraft fuselage, the interior trim parts 2, 3, 4, 5, 6 have brackets 10 for connection to and for force introduction into the aircraft cell. The respective force introduction points into the aircraft structure are predetermined by the manufacturer of the aircraft or are to be formed accordingly. Through the mounting brackets 10, during assembly of the interior trim panels 2, 3, 4, 5, 6, these are bolted to the aircraft compartment or otherwise connected to the aircraft compartment.
    According to the invention, the interior trim parts 2, 3, 4, 5, 6 are provided with a support structure and have one or more support positions 9, which are designed for load-bearing.
    The support structure of the load-bearing interior trim parts 2, 3, 4, 5, 6 is formed by the internal structure of the interior trim parts 2, 3, 4, 5, 6 and may be realized by various means known to those skilled in the art, e.g. through choice of material, wall thickness, profile design etc.
    In addition, the interior trim parts 2, 3, 4, 5, 6 may have reinforcements or ribbing to increase rigidity.
    Thus, the interior trim parts may be reinforced by carbon fiber fabrics with a tensile strength of about 900 MPa, with glass fiber about 600 MPa can be achieved.
    In a quasi-isotropic design, carbon fiber may have an E-modulus of 40 GPa, while in glass fiber it may be about 10 GPa.
    The stated exemplary values are highly dependent on the fiber used, but are much higher than conventional interior trim panel materials.
    The support positions 9 associated with the support structure of the interior trim part allow for picking up loads acting on the support positions 9. These loads are e.g. medical devices, screens, instruments, etc. that may be suspended in operation at these mounting positions 9.
    As shown in Fig.l, the support positions 9, which are shown in Fig.l as dots, - pre-fabricated in raster-shaped arrangement - present from the outside - may be pre-fabricated so that they are selectable as needed and already integrated in the interior trim part. The mounting positions 9 are provided for this purpose below the surface of the interior trim parts 2, 3, 4, 5, 6 and can be rendered functional by breaking the corresponding surface area. They are first visible through this process.
    A variant of such a mounting position 9 is shown in detail in Fig.5. The interior trim part 6 has at this point two interconnected layers 27, 28, the layer 27 having a pierceable wall weakening 26, below which is formed a cavity including a screw thread 25 so that when penetrated wall weakening the underlying threaded hole is exposed, in which from outside to suspension purposes a threaded bolt (not shown) can be screwed. The threaded hole is embedded in the wall 28 so that the forces introduced externally over the threaded bolt are dissipated via the support structure of the inner trim piece 6 and subsequently via the aircraft vehicle cell.
    In this way, the support positions 9 are formed by thread inserts which are integrated in the interior trim parts 2, 3, 4, 5, 6, wherein the threaded inserts for
    Recording of support devices are formed.
    With a grid-like arrangement of the mounting positions 9, as shown in Fig.l, a variable attachment of, in particular medical equipment devices is made possible.
    Such as. 2, 3, 4, 5, 6 are shaped and matched to one another and provided at connection points with suitable connecting elements 15 that they are positively and non-positively connected to each other in the assembled state in Fig. L, 2 and 3.
    Due to the non-positive connection of
    Interior trim parts 2, 3, 4, 5, 6 turns one
    Bonding effect, whereby the assembled assembly has an increased load capacity.
    Thus, the interior trim parts 2, 4, 6 in the connected state (Fig.l) form a U-shaped or arcuate
    Cross-section, by each of the upper edge region of the inner lining parts 2 and 6 with opposite
    Transverse end of the interior trim part 4 are frictionally connected. Through the further connection of the
    Interior trim part 3 with the side areas of
    Interior trim parts 2, 4, 6 still increase the rigidity of the assembly.
    Due to the composite effect achieved by this, no restraining by a bottom plate is required, so that in
    Floor area of the aircraft cell, a bottom plate 20 (Figure 4) is mounted with a small wall thickness and thus low weight, which is not in frictional connection with the interior trim parts 2, 3, 4, 5, 6. On the bottom plate are holders, e.g. B. for a stretcher.
    FIG. 6 shows, by way of example, a force transmission from an interior trim part 2, 3, 4, 5, 6 according to the invention into a wall 50 of the aircraft cell, which is mounted over the bracket 10 attached to the interior trim part 2, 3, 4, 5, 6 and to the wall 50 Bracket 10 ', which with each other, for example are realized via a screw 101, is realized. Such or similar force introduction points are provided in a plurality of locations in order to produce the interior trim parts 2, 3, 4, 5, 6 or 6 according to the invention. To connect the component group according to the invention with the airframe so that the loads acting on the inner cover parts are absorbed by the latter.
    权利要求:
    Claims (13)
    [1]
    Patent claims 1. An interior trim part (2, 3, 4, 5, 6) for an aircraft compartment, characterized in that it has a support structure, wherein at least one support position (9) is provided on the inside, which is designed for load application.
    [2]
    An interior trim part according to claim 1, characterized in that it has below the surface a plurality of selectable support positions (9) in a grid-like arrangement to enable variable attachment of, in particular, medical equipment.
    [3]
    An interior trim part according to claim 2, characterized in that the support positions (9) are formed by concealed threaded inserts integrated in the interior trim parts (2, 3, 4, 5, 6), the threaded inserts being adapted to receive support devices.
    [4]
    4. interior trim part according to one of claims 1 to 3, characterized in that it has to increase the rigidity reinforcements or ribbing.
    [5]
    5. Prefabricated assembly with one or more interior trim parts according to one of claims 1 to 4, characterized in that the interior trim parts (2, 3,4, 5, 6) connection points (15), where they are mutually positively connected.
    [6]
    6. Prefabricated assembly according to claim 5, characterized in that the interior trim parts (2, 3, 4, 5.6) holding bracket (10) for connection to and for force introduction into the aircraft cell.
    [7]
    7. Prefabricated assembly according to claim 5 or 6, characterized in that the inner lining parts (2, 3, 4, 5,6) on the brackets (10) are screwed or connectable to the aircraft cell.
    [8]
    8. Prefabricated assembly according to one of claims 6 or 7, characterized in that the inner lining parts (2, 3,4, 4, 5, 6) have at least two side parts and a ceiling part, which are connectable to a U-shaped cross-section.
    [9]
    Prefabricated assembly according to one of claims 6 to 8, characterized in that the inner lining parts (2, 3, 4, 5, 6) have below the surface a plurality of selectable mounting positions (9) in a grid-like arrangement in order to allow variable attachment of, in particular, to enable medical equipment.
    [10]
    Prefabricated assembly according to any one of claims 6 to 9, characterized in that a floor panel (20) of low wall thickness, which is not in frictional connection with the interior trim parts (2, 3, 4, 5, 6), is mounted in the floor area of the aircraft compartment.
    [11]
    11. Prefabricated assembly according to claim 10, characterized in that the bottom plate brackets, for. B. for a stretcher has.
    [12]
    12. Aircraft with one or more interior trim parts mounted in the airframe or a prefabricated subassembly according to one of claims 1 to 11.
    [13]
    An aircraft according to claim 12, characterized in that it is a helicopter, in particular a rescue helicopter, or an aircraft.
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    引用文献:
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    法律状态:
    优先权:
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