A trim element for the edge of an aircraft seat shell, manufacturing process and installation method for such an element

Abstract

The invention relates to a flexible trim element (100) for an edge (210) of an aircraft seat shell (200), comprising an assembly of at least two long, flexible, flat cutouts (110a, 110b, 110c) joined together by their respective longitudinal edges so that the assembly has a three-dimensional shape conforming to an edge of an aircraft seat shell. The invention also relates to a method (300) for manufacturing such a trim element, as well as a method (400) for installing such a trim element on an aircraft seat shell. (See Figure 1 for abbreviations.)

Description

Title of the invention: Element for covering an edge of an aeronautical seat shell, manufacturing method and method for installing such an element Technical field

[0001] The field of the invention is that of aeronautical seats, in particular passenger seats, elements for covering their shells, methods of manufacturing and installing such elements.

[0002] More specifically, the invention relates to a covering element for an edge of an aeronautical seat shell, intended for the purposes of finishing and padding or upholstering said edge.

[0003] Thus, the invention finds direct applications in the aeronautical field, however it can also be applied to any other related industrial field. STATE OF THE ART

[0004] An aircraft seat shell is a three-dimensional structure of complex shape, generally made of plastic, composite or metal material.

[0005] In the design of an aeronautical seat comprising such a shell, the finish of the seat at the edges of the shell is of capital importance, both in terms of the protection of the edges of the shell, and in terms of the aesthetic appearance.

[0006] Various techniques for covering elements for aeronautical seat shells are known from the prior art, as well as their associated manufacturing methods. Such covering elements are sometimes also called "cap edge" in English terminology.

[0007] According to a first known technique, metal cladding elements are obtained by machining a metal material from a solid. Such a technique, although providing a "high-end" appearance, has the disadvantage of a high material and machining cost, and that of a significant mass. This latter aspect is particularly critical in the field of aeronautics, where any possible savings in mass are sought. In addition, such metal cladding elements do not allow the covering of an edge of a hull in one piece, due to the excessive volume of metal material that would have to be machined from the solid. This results in the need to make junctions between several cladding elements, and to adjust the cladding elements together, which represents a significant disadvantage in terms of aesthetics and economic costs during manufacturing and assembly.

[0008] According to a second known technique, composite cladding elements are obtained by molding, for example by injection or by thermoforming. This type of cladding elements has the disadvantage of requiring high investments, due to the high economic cost of the molds. In addition, the molds must be renewed for each new shape of cladding element to be manufactured.

[0009] According to a third known technique, trim elements made of plastic, in particular polyvinyl chloride (PVC), or silicone, are obtained by extrusion of these materials. However, although less expensive, these techniques are not very aesthetic and only allow the front part of the edge of the seat shell to be covered, without allowing the edges of the shell adjoining the edge of the shell to be covered. In other words, these techniques only allow the manufacture of trim elements of simple section, allowing only a basic finish.

[0010] Thus, none of the current systems can simultaneously meet all the required needs, namely to propose a technique for light and aesthetic covering elements, which allow the covering of a seat shell edge as well as the edges of the shell adjoining the edge, while being inexpensive, with minimal loss of material. Statement of the invention

[0011] The present invention aims to remedy all or part of the drawbacks of the state of the art cited above.

[0012] To this end, the invention relates to a flexible covering element for an edge of an aeronautical seat shell, composed of an assembly of at least two elongated, flexible and flat cutouts, secured one to one by respective longitudinal edges so that the assembly has a three-dimensional shape conforming to an edge of an aeronautical seat shell.

[0013] By these arrangements, a covering element made in a simple manner from a limited number of parts / elements can be obtained. An entire edge of an aeronautical seat shell can be covered from only two cutouts, in a minimal configuration. The flexible nature of the cutouts makes it possible to obtain a covering element which is itself flexible, which adapts very precisely to the edge of the aeronautical seat, in addition to providing a pleasant aesthetic and haptic appearance for a user. In addition, the material from which the cutouts are obtained being flexible and flat, the latter can be easily stored, for example in the form of a roll, and the cutouts themselves, as well as the covering elements obtained, can be stored very easily due to their flexible nature.

[0014] In summary, the characteristics of the covering element according to the invention make it possible to obtain a light and aesthetic covering element, completely covering the edge of the seat shell as well as at least one edge of the shell adjoining the edge, while being inexpensive to manufacture, due to its simple design.

[0015] The invention also relates to the following complementary preferred variants, freely combinable in any technically effective combination.

[0016] More particularly, according to a preferred variant, said three-dimensional shape corresponds to the shape generated by the translation of a cross-section of the covering element along an open path of the three-dimensional space, said open path corresponding to the path followed by an edge of an aeronautical seat shell.

[0017] Thus, a covering element is obtained which fits very precisely to the edge of the seat. It is thus possible to place the covering element on the edge with very little play, contributing to the effective protection of the edge, and further improving the aesthetic and haptic rendering. In addition, in such a configuration, the covering element has the advantage of being continuous along the edge, which reinforces its hold on the edge, and further improves the aesthetic rendering.

[0018] According to a preferred variant, the covering element is composed of three elongated cutouts, the covering element having a substantially U-shaped cross-section.

[0019] In this way, the edge as well as the two edges of the shell adjoining the edge are covered by the covering element. Thus, the protection and the aesthetic appearance of the seat shell are further reinforced and improved.

[0020] According to a preferred variant, the cutouts are joined together by sewing, welding, or gluing.

[0021] According to a preferred variant, the cutouts are composed of a complex of several flat flexible materials.

[0022] Thus, it is possible to combine materials having different mechanical and aesthetic properties. It is thus possible to obtain a covering element adapted to different uses and different ranges of seats.

[0023] According to a preferred variant, the cutouts comprise a woven material, and / or leather, and / or imitation leather.

[0024] Such materials correspond to flexible and flat materials which can be easily cut and assembled, and which have mechanical and aesthetic characteristics sought after in the aeronautical field in particular.

[0025] According to a preferred variant, at least one cutout comprises an elongated reinforcement fixed on an internal surface of said cutout.

[0026] Thus, it is possible to reinforce the covering element while preserving its external appearance. Greater longevity of the covering element, and thus of the seat, is obtained.

[0027] The invention also relates to an aeronautical seat shell comprising a covering element, said covering element being fixed to an edge of the shell. aeronautical headquarters.

[0028] The invention also relates to a method of manufacturing a covering element comprising: - a step of flat cutting of a flexible and flat material, so as to obtain said elongated cuts, - a step of assembling said cutouts one by one by respective longitudinal edges.

[0029] Thus, the covering element according to the invention can be obtained from a limited number of steps. In addition, said steps have the advantage of being particularly simple technically, and can be carried out quickly and do not require the intervention of a qualified operator.

[0030] In summary, the method makes it possible to obtain a cladding element having the advantages mentioned above, while itself having the advantage of being simple and inexpensive.

[0031] According to a preferred variant, the method further comprises a step of forming a hem, formed on at least one longitudinal edge of at least one cutout, said step preceding the assembly step.

[0032] Thus, fraying of the longitudinal edges of the cutout can be avoided, and a better aesthetic result is obtained.

[0033] According to a preferred variant, the method further comprises a reinforcement step in which a reinforcement is fixed to an internal surface of a cutout, said step preceding the assembly step.

[0034] The invention also relates to a method for installing a covering element on an aeronautical seat shell, comprising: - a preparation step, in which a bonding agent is applied to the edges adjoining the edge of the hull, - a laying step, in which the cladding element is placed on the edge.

[0035] According to a preferred variant, the method further comprises a step of placing a foam on the edge of the hull, said step preceding the placing step. BRIEF DESCRIPTION OF THE FIGURES

[0036] Other advantages, aims and particular characteristics of the present invention will emerge from the following non-limiting description of at least one particular embodiment of the devices and methods which are the subject of the present invention, with reference to the appended drawings, in which: • [Fig.l] is a particular example of the production of a covering element for an edge of an aeronautical seat shell; • [Fig.2] is a front sectional view of the cladding element arranged in vis- with respect to an edge of an aeronautical seat shell according to a particular example of embodiment; • [Fig.3] is a perspective sectional view of the cladding element arranged opposite an edge of an aeronautical seat shell according to a particular example of embodiment; • [Fig.4] is a set of cutouts in a disassembled state; • [Fig.5] is a detailed view of an example of the result obtained after sewing the cutouts between them; • [Fig.6] is a perspective view of the cladding element, having a three-dimensional curvilinear shape; • [Fig.7] is a block diagram of a manufacturing process for an element dressing; • [Fig.8] is a block diagram of a process for installing an element covering on an aircraft seat edge. DETAILED DESCRIPTION OF THE INVENTION

[0037] The present description is given without limitation, each characteristic of an embodiment being able to be combined with any other characteristic of any other embodiment in an advantageous manner.

[0038] It should be noted, from now on, that the figures are not to scale. Example of a particular embodiment

[0039] [Fig.l] represents a covering element 100 of a shell edge 200 of an aeronautical seat according to a particular embodiment of the invention.

[0040] The covering element 100 is shaped to the shape of the edge so as to be able to cover it. By "shaped" is meant the fact that the covering element is adapted or configured to cover exactly, that is to say with a small clearance, an edge of an aeronautical seat. Thus, when it is arranged on the edge, the covering element 100 allows the finishing of the edge and consequently of the seat shell 200. It is also understood that a covering element 100 is specially designed to cover a particular shell 200, the shapes of the shells 200 being able to vary.

[0041] Figures 2 and 3 show a sectional view of the covering element 100 arranged opposite an edge 210 of the shell 200 of an aeronautical seat according to a particular embodiment of the invention, respectively from the front and in perspective. In addition, in [Fig. 3], the covering element 100 is shown opposite the edge of the shell 200, without however being arranged on the edge.

[0042] The covering element 100 comprises three elongated cutouts 110a, 110b and 110c. The cutouts 110a, 110b and 110c are obtained from a flexible and flat material, such as leather, imitation leather or a woven material, presented in the form of a sheet, sheet, film, etc. A cutout can also be made from several sub-cutouts, of different or different material, for example joined to each other. The cutouts 110a, 110b and 110c can also each be of a different material. The cutouts 110a, 110b and 110c can also be obtained from a complex of several flexible materials. The material chosen is preferably a material that is particularly resistant to abrasion, and / or fire resistant.

[0043] The three cutouts 110a, 110b and 110c are assembled to each other, the assembly of the three cutouts 110a, 110b and 110c forming the essential part of the covering element 100. In the non-limiting example shown in Figures 2 and 3, the three cutouts 110a, 110b and 110c are assembled to each other substantially perpendicularly, any other angle however being able to be delimited between two cutouts. A longitudinal edge of a cutout 110a, 110b or 110c is secured to at most one other longitudinal edge of a cutout 110a, 110b or 110c. In other words, the cutouts 110a, 110b and 110c are assembled one by one along their longitudinal edges. In the present embodiment, the cutout 110b corresponds to a central cutout capable of covering the edge 210, and the cutouts 110a and 110c correspond to lateral cutouts arranged on either side of the central cutout 110b, and are capable of covering the edges adjoining the edge 210.

[0044] The aforementioned assembly gives a cross-sectional shape to the covering element 100 corresponding substantially to a U-shape (inverted in FIGS. 2 and 3), more or less flared, when the covering element 100 is essentially made up of three cutouts.

[0045] It is easily understood that when the covering element 100 comprises two cutouts, the shape of the cross-section corresponds substantially to that of a V, more particularly of an L when the cutouts are assembled perpendicularly.

[0046] In the same way, the covering element 100 may comprise more than three cutouts, such as for example four cutouts, the shape of the cross-section then corresponding substantially to that of a W or an M, for example.

[0047] [Fig. 4] shows a set of cutouts, including in particular the three cutouts 110a, 110b and 110c in a disassembled state. The cutouts 110a, 110b and 110c take the form of curvilinear strips, that is to say they are in the form of strips of flat material extending substantially in a plane along a curvilinear path in this same plane. In the present exemplary embodiment, the lateral cutouts 110a and 110c take substantially the same form.

[0048] In the example of [Fig.4], the cutouts 110a, 110b and 110c follow a curvilinear path substantially in the shape of a J and an L, however other paths can be followed, such as an S-shaped path, a U-shaped path, a C-shaped path, etc.

[0049] The cutouts 110a, 110b and 110c are assembled by sewing in the present embodiment. Other assembly techniques may also be used, such as gluing or welding, for example.

[0050] The cutouts 110a, 110b and 110c are preferably sewn together at the longitudinal edges by seams 114. A seam 114 can be single or double depending on the desired robustness, the material of the cutouts, etc.

[0051] Longitudinal edge means the edge of a cutout extending parallel to the path followed by the covering element 100. The longitudinal edges are generally the longest edges of a cutout.

[0052] Advantageously, the seam 114 between two cutouts is made at a distance from the longitudinal edge, so as to be able to form a finishing hem with the excess material at the longitudinal edge. The hem obtained, as shown in Figures 2, prevents the longitudinal edges of the cutout from fraying, and provides a better aesthetic result.

[0053] [Fig. 5] shows a detailed view of an example of the result obtained after sewing the cutouts 110a, 110b and 110c together, and forming the hems. The seams 114 are only very slightly visible, while seams 115 for forming the hems are visible and contribute to the attractive aesthetic appearance of the covering element 100.

[0054] By assembling the cutouts 110a, 110b and 110c, the covering element 100 acquires a three-dimensional curvilinear shape, as represented by the example of the covering element 100 of [Fig. 6]. More particularly, the shape of the covering element 100 corresponds substantially to the shape obtained by the translation of the cross-section (U-shaped in the present exemplary embodiment) along a path open in the three-dimensional space, said path having at all points the same curvature as an external surface of the edge 210 of the shell 200. More specifically, this path corresponds to the path followed by the edge 210 of the shell 200 of the aeronautical seat. Thus, the covering element 100 is capable of being arranged on the edge 210 so as to cover the latter, the covering element 100 being shaped to the shape of the edge 210.

[0055] It should be noted that the cross-section can be variable along the open path of space, i.e. the three-dimensional curvilinear shape can be of variable cross-section. In other words, this means that the width of the cutouts 110a, 110b and 110c, and in particular of the cutout 110b, is variable. It is thus possible to adapt to a seat shell which would have a non-constant thickness.

[0056] Such a three-dimensional and curvilinear shape of the covering element 100 is obtained by choosing the particular shape of each of the cutouts 110a, 100b and 110c. Thus, each edge 210 of the shell corresponds to a set of cutouts, comprising at least two initially flat cutouts, of different shape, making it possible to obtain a three-dimensional assembly.

[0057] As shown in Figures 2 and 3, the lateral cutouts 110a and 110c optionally comprise reinforcements 111a and 111c. The reinforcements 111a and 111c are arranged on an internal surface of the cutouts 110a and 110c. The internal surface of said cutouts corresponds to the surface oriented towards the edge 210 and its adjoining edges. In other words, the internal surface is the surface oriented in opposition to an external surface which is visible when the covering element 100 is arranged on the shell 200 of the aeronautical seat.

[0058] Similar to cutouts 110a, 110b and 110c, reinforcements 11a and 11c are in the form of flat curvilinear strips, in a disassembled state, as shown in [Fig.4].

[0059] The reinforcements 111a and 111c are preferably made of a stiffening material, which nevertheless remains sufficiently flexible to allow the cutouts to be assembled together. Such a material may, for example, be a laminate, for example of the Isolvolta brand (registered trademark), preferably of reference B50. An equivalent, such as a thermoplastic film, may also be used. The thickness of the material used is preferably equal to substantially 0.5 millimeters.

[0060] The reinforcements 111a and 111c may be fixed to the internal surfaces of the cutouts 110a and 110c by means of any suitable technique, and preferably by gluing. The gluing may be carried out by applying glue, or by applying a “double-sided” type adhesive tape, i.e. one having a sticky mass on each of its faces.

[0061] The covering element 100 can be fixed to the shell 200 by means of any suitable technique. Preferably, the covering element 100 is glued to the shell 200. More precisely, the internal surfaces of the cutouts 110a and 110c are glued to the edges adjoining the edge 210, as shown in [Fig. 3], on which beads of glue 112 are shown. In [Fig. 2], the glue 112 is distributed over the internal surface of the cutouts 110a and 110c, so as to ensure firm holding of the covering element 100 on the shell 200. Alternatively, a double-sided adhesive strip can also be used.

[0062] Advantageously, a layer 113 of foam is arranged between the edge 210 and the central cutout 110b. Optionally, the layer 113 of foam is glued to the edge 210 and / or the internal surface of the central cutout 110b. Preferably, the glue used is water-based.

[0063] The covering element 100 is obtained by a manufacturing method 300 which is described below, illustrated by the block diagram of [Fig.7].

[0064] During a flat cutting step 310, the cutouts 110a, 110b and 110c are obtained by flat cutting of a flexible and flat, or flattened, material, such as a sheet of flexible material or a sheet of flexible material.

[0065] Of course, the cutting can be optimized so as to minimize waste of unusable materials, for example by using cutting optimization software during the programming phase of a cutting machine.

[0066] Optionally, during a step 320 of forming a hem, a hem is formed on the longitudinal edge of a cutout, in accordance with what was explained above.

[0067] Optionally, during a reinforcement step 330, a reinforcement is fixed to an internal surface of a cutout. For example, the reinforcement can be fixed by gluing.

[0068] The reinforcement step 330 is shown following the step 320 of forming a hem in [Fig.7], however these steps can also be reversed indifferently.

[0069] During an assembly step 340, the cutouts 110a, 110b and 110c are joined together, preferably by sewing. The assembly is carried out at the longitudinal edges of the cutouts 110a, 110b and 110c, which are joined one by one.

[0070] Of course, the manufacturing method 300 can be generalized to any other number of cuts.

[0071] Furthermore, a method 400 for installing a covering element 100 on an aircraft seat shell 200 is also described below, illustrated by the block diagram of [Fig.8].

[0072] During preparation step 410, a bonding means is applied to the edges adjoining the edge 210 of the shell 200. According to one variant, a double-sided adhesive strip is placed on the edges adjoining the edge 210, while according to another variant, a masking adhesive strip is placed on the edges adjoining the edge 210, so as to allow good application of a bead of glue 112 on said adjoining edges.

[0073] Optionally, during a step 415 of laying a foam, the foam 113 is laid on the edge 210. Preferably, the foam is laid using a holding tool in which sections of foam are placed, and via which a substantially uniform pressure can be applied. In this way, a regular laying of foam 113 can be ensured.

[0074] During a laying step 420, the covering element 100 is laid on the edge 210 (covered or not with foam 113). Preferably, the covering element 100 is laid starting from a strongly curved portion of the edge 210. During the step 420 of installation, in particular the lateral cutouts 110a and 110c are smoothed on the edges adjoining the edge 210, so as to obtain an aesthetic transition between a cutout and the shell 200. Preferably, the covering element 100 is held in position by a suitable tool (by clamping, under the effect of a weight, etc.) until the glue 112 dries.

Claims

Claims

1. Flexible covering element (100) for an edge (210) of an aeronautical seat shell (200), characterized in that it is composed of an assembly of at least two elongated, flexible and flat cutouts (110a, 110b, 110c), secured one to one by respective longitudinal edges so that the assembly has a three-dimensional shape conforming to an aeronautical seat shell edge.

2. A trim element (100) according to claim 1, said three-dimensional shape corresponding to the shape generated by the translation of a cross-section of the trim element along an open path of three-dimensional space, said open path corresponding to the path followed by an edge (210) of an aeronautical seat shell (200).

3. A covering element (100) according to any one of claims 1 or 2, composed of three cutouts (110a, 110b, 110c), the covering element having a substantially TT-shaped cross-section

4. U. Covering element (100) according to any one of claims 1 to 3, in which said cutouts (110a, 110b, 110c) are secured to each other by sewing, welding, or gluing.

5. Covering element (100) according to any one of claims 1 to 4, in which the cutouts (110a, 110b, 110c) are composed of a complex of several flat flexible materials.

6. A trim element (100) according to any one of claims 1 to 5, wherein the cutouts (110a, 110b, 110c) comprise a woven material, and / or leather, and / or imitation leather.

7. A covering element (100) according to any one of claims 1 to 6, wherein at least one cutout (110a, 110c) comprises an elongated reinforcement (111a, 111c) fixed to an internal surface of said cutout (110a, 110c).

8. Aircraft seat shell (200) comprising a covering element (100) according to one of claims 1 to 7, said covering element (100) being fixed to an edge (210) of the aircraft seat shell (200).

9. Method (300) for manufacturing a covering element (100) according to any one of claims 1 to 7, characterized in that it comprises: - a step (310) of flat cutting of a flexible and flat material, so as to obtain said elongated cutouts (110a, 110b, 110c), - a step (340) of assembling said cutouts (110a, 110b, 110c) one by one by respective longitudinal edges.

10. Method (300) according to claim 9, further comprising a step (320) of forming a hem, formed on at least one longitudinal edge of at least one cutout (110a, 110b, 110c), said step (320) preceding the assembly step (340).

11. A method (300) according to any one of claims 9 or 10, further comprising a reinforcing step (330) in which a reinforcement (111a, 111c) is fixed to an internal surface of a cutout (110a, 110c), said step (320) preceding the assembly step (340).

12. Method (400) for installing a covering element (100) according to any one of claims 1 to 7 on an aeronautical seat shell (200), comprising: - a preparation step (410), in which a bonding means (112) is applied to the edges adjoining the edge (210) of the shell (200), - an installation step (420), in which the covering element (100) is placed on the edge (210).

13. Method (400) according to claim 12, further comprising a step (415) of laying a foam (113) on the edge (210) of the shell (200), said step (415) preceding the laying step (420).

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