LINING ELEMENT OF AN EDGE OF AN AERONAUTICAL SEAT SHELL, METHOD FOR MANUFACTURING AND METHOD FOR SETTING UP SUCH AN ELEMENT

Abstract

A flexible element for lining an edge of an aeronautical seat shell, made up of an assembly of at least two elongate, flexible and planar cut pieces, secured together by respective longitudinal boundaries so that the assembly has a three-dimensional shape matching with an edge of an aeronautical seat shell.

A method for manufacturing such a lining element, as well as a method for setting up such a lining element over an aeronautical seat shell.

Claims

1. A lining element that is flexible for lining an edge of an aeronautical seat shell, characterized in that it is made up of an assembly of at least two elongate, flexible and planar cut pieces, secured together by respective longitudinal boundaries so that the assembly has a three-dimensional shape matching with an edge of an aeronautical seat shell.

2. The lining element according to claim 1, said three-dimensional shape corresponding to the shape generated by the translation of a cross-section of the lining element along an open path of the three-dimensional space, said open path corresponding to the path covered by an edge of an aeronautical seat shell.

3. The lining element according to claim 1, made up of three cut pieces, the lining element having a substantially U-like shaped cross-section.

4. The lining element according to claim 1, wherein said cut pieces are secured together by sewing, welding, or gluing.

5. The lining element according to claim 1, wherein the cut pieces are made up of a lamination of several planar flexible materials.

6. The lining element according to claim 1, wherein the cut pieces comprise a woven material, and/or leather, and/or leatherette.

7. The lining element according to claim 1, wherein at least one cut piece comprises an elongate reinforcement fastened on an inner surface of said cut piece.

8. An aeronautical seat shell comprising the lining element according to claim 1, said lining element being fastened over an edge of the aeronautical seat shell.

9. A method for manufacturing the lining element according to claim 1, characterized in that it comprises: a step of flat cutting a flexible and planar material, so as to obtain said elongate cut pieces, a step of assembling said cut pieces together by respective longitudinal boundaries.

10. The method according to claim 9, further comprising a step of forming a hem, formed over at least one longitudinal boundary of at least one cut piece, said step preceding the assembly step.

11. The method according to claim 9, further comprising a reinforcement step in which a reinforcement is fastened over an inner surface of a cut piece, said step preceding the assembly step.

12. A method for setting up the lining element according to claim 1 over an aeronautical seat shell, comprising: a preparation step, in which a bonding means is applied over the boundaries contiguous to the edge of the shell, a set-up step, in which the lining element is set up over the edge.

13. The method according to claim 12, further comprising a step of setting up a foam over the edge of the shell, said step preceding the set-up step.

Description

BRIEF DESCRIPTION OF THE FIGURES

[0041] Other advantages, aims and particular features of the present disclosure will appear from the following non-limiting description of at least one particular embodiment of the devices and methods objects of the present disclosure, with reference to the appended drawings, wherein:

[0042] FIG. 1 is a particular embodiment of the element for lining an edge of an aeronautical seat shell;

[0043] FIG. 2 is a sectional front view of the lining element disposed opposite an edge of an aeronautical seat shell according to a particular embodiment;

[0044] FIG. 3 is a sectional perspective view of the lining element disposed opposite an edge of an aeronautical seat shell according to a particular embodiment;

[0045] FIG. 4 is a set of cut pieces in a disassembled state;

[0046] FIG. 5 is a detailed view of an example of a result obtained after sewing the cut pieces together;

[0047] FIG. 6 is a perspective view of the lining element, having a three-dimensional curvilinear shape;

[0048] FIG. 7 is a flowchart of a method for manufacturing a lining element;

[0049] FIG. 8 is a flowchart of a method for setting up a lining element over an edge of an aeronautical seat.

DETAILED DESCRIPTION

[0050] This description is given on a non-limiting basis, each feature of an embodiment may advantageously be combined with any other feature of any other embodiment.

[0051] It should be noted, as of now, that the figures are not to scale.

Example of a Particular Embodiment

[0052] FIG. 1 represents an element 100 for lining an edge of an aeronautical seat shell 200 according to a particular embodiment of the disclosure.

[0053] The lining element 100 matches with the shape of the edge so as to be able to cover it. By “matching with”, it should be understood the fact that the lining element is adapted or configured to tightly cover, i.e. with a small clearance, an edge of an aeronautical seat. Thus, when it is disposed over the edge, the lining element 100 allows finishing the edge and consequently the seat shell 200. It should also be understood that a lining element 100 is designed specifically to cover a particular shell 200, the shapes of the shells 200 can vary.

[0054] FIGS. 2 and 3 represent a sectional view of the lining element 100 disposed opposite an edge 210 of an aeronautical seat shell 200 according to a particular embodiment of the disclosure, respectively in front view and in perspective view. In addition, in FIG. 3, the lining element 100 is represented opposite the edge of the shell 200, yet without being disposed over the edge.

[0055] The lining element 100 includes three elongate cut pieces 110a, 110b and 110c. The cut pieces 110a, 110b and 110c are obtained from a flexible and planar material, such as leather, leatherette or a woven material, supplied in the form of a drape, a sheet, a film, etc. A cut piece may also be made from several cut sub-pieces, made of different materials or not, for example secured together. The cut pieces 110a, 110b and 110c may also be made each of a different material. The cut pieces 110a, 110b and 110c may also be obtained from a lamination of several flexible materials. Preferably, the selected material is a material that is particularly abrasion-resistant, and/or fire-resistant.

[0056] The three cut pieces 110a, 110b and 110c are assembled together, the assembly of the three cut pieces 110a, 110b and 110c forming the bulk of the lining element 100. In the non-limiting example represented in FIGS. 2 and 3, the three cut pieces 110a, 110b and 110c are assembled together substantially perpendicularly, any other angle may nonetheless be delimited between two cut pieces. A longitudinal boundary of a cut piece 110a, 110b or 110c is secured at most to one other longitudinal boundary of a cut piece 110a, 110b or 110c. In other words, the cut pieces 110a, 110b and 110c are assembled one after another along their longitudinal boundaries. In the present embodiment, the cut piece 110b corresponds to a central cut piece able to cover the edge 210, and the cut pieces 110a and 110c correspond to lateral cut pieces disposed on either side of the central cut piece 110b, and are able to cover the boundaries contiguous to the edge 210.

[0057] The aforementioned assembly confers a cross-sectional shape of the lining element 100 corresponding substantially to a U-like shape (inverted in FIGS. 2 and 3), more or less flared, when the lining element 100 is made up essentially of three cut pieces.

[0058] It should be easily understood that when the lining element 100 includes two cut pieces, the shape of the cross-section corresponds substantially to that of a V-like shape, more particularly of a L-like shape when the cut pieces are assembled perpendicularly.

[0059] In the same manner, the lining element 100 may include more than three cut pieces, such as four cut pieces, the shape of the cross-section then corresponding substantially to that of a W-like shape or of a M-like shape, for example.

[0060] FIG. 4 represents a set of cut pieces, comprising in particular the three cut pieces 110a, 110b and 110c in a disassembled state. The cut pieces 110a, 110b and 110c are in the form of curvilinear strips, i.e. they are in the form of strips of a planar matter extending substantially in a plane according to a curvilinear pattern in this same plane. In the present embodiment, the lateral cut pieces 110a and 110c have substantially the same shape.

[0061] On the example of FIG. 4, the cut pieces 110a, 110b and 110c follow a J-like and L-like shaped curvilinear pattern, nonetheless other patterns may be followed, such as a S-like, U-like, C-like shaped pattern, etc.

[0062] The cut pieces 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.

[0063] Preferably, the cut pieces 110a, 110b and 110c are sewn together at the longitudinal boundaries by seams 114. A seam 114 may be simple or double depending on the desired robustness, the material of the cut pieces, etc.

[0064] By longitudinal boundary, it should be understood the boundary of a cut piece extending parallel to the path followed by the lining element 100. In general, the longitudinal boundaries are the longest boundaries of a cut piece.

[0065] Advantageously, the seam 114 between two cut pieces is made at a distance from the longitudinal boundary, so as to be able to form a finishing hem with the excess matter at the longitudinal boundary. The obtained hem, as represented in FIGS. 2, prevents fraying of the longitudinal boundaries of the cut piece, and confers a better aesthetic appearance.

[0066] FIG. 5 represents a detailed view of an example of a result obtained after sewing the cut pieces 110a, 110b and 110c together, and forming the hems. The seams 114 are barely visible, whereas seams 115 allowing forming the hems are visible and contribute to the aesthetically-pleasant appearance of the lining element 100.

[0067] By assembly of the cut pieces 110a, 110b and 110c, the lining element 100 acquires a three-dimensional curvilinear shape, as represented by the lining element 100 example of FIG. 6. More particularly, the shape of the lining element 100 corresponds substantially to the shape obtained by translation of the cross-section (U-like shaped in the present embodiment) along an open path in the three-dimensional space, said path having the same curvature as an outer surface of the edge 210 of the shell 200 at every point. More specifically, this path corresponds to the path followed by the edge 210 of the aeronautical seat shell 200. Thus, the lining element 100 can be disposed over the edge 210 so as to cover the latter, the lining element 100 matching with the shape of the edge 210.

[0068] It should be pointed out that the cross-section may be variable along the open path of the space, i.e. the three-dimensional curvilinear shape may have a variable cross-section. In other words, this means that the width of the cut pieces 110a, 110b and 110c, and in particular of the cut piece 110b, is variable. Thus, it is possible to adapt to a seat shell that would have a non-constant thickness.

[0069] Such a three-dimensional and curvilinear shape of the lining element 100 is obtained through the selection of the particular shape of each of the cut pieces 110a, 110b and 110c. Thus, a set of cut pieces corresponds to each edge 210 of the shell, including at least two cut pieces that are initially planar, with different shapes, allowing obtaining a three-dimensional assembly.

[0070] Optionally, as represented in FIGS. 2 and 3, the lateral cut pieces 110a and 110c include reinforcements 111a and 111c. The reinforcements 111a and 111c are disposed over an inner surface of the cut pieces 110a and 110c. The inner surface of said cut pieces corresponds to the surface oriented towards the edge 210 and its contiguous boundaries. In other words, the inner surface is the surface oriented opposite to an outer surface which is visible when the lining element 100 is disposed over the aeronautical seat shell 200.

[0071] Like the cut pieces 110a, 110b and 110c, the reinforcements 111a and 111c are in the form of planar curvilinear strips, in a disassembled state, as represented in FIG. 4.

[0072] Preferably, the reinforcements 111a and 111c are made of a stiffening material, yet still remaining flexible enough to enable assembly of the cut pieces together. For example, such a material may be a laminate, for example of the Isolvolta brand (registered trademark), preferably the reference B50. An equivalent, such as a thermoplastic film, may also be used. Preferably, the thickness of the used material is equal to substantially 0.5 millimeters.

[0073] The reinforcements 111a and 111c may be fastened on the inner surfaces of the cut pieces 110a and 110c by means of any suitable technique, and preferably by gluing. Gluing may be performed by depositing glue, or by setting up a “double-sided” type adhesive tape, i.e. having a bonding side on each of its faces.

[0074] The lining element 100 can be fastened over the shell 200 by means of any suitable technique. Preferably, the lining element 100 is glued over the shell 200. More specifically, the inner surfaces of the cut pieces 110a and 110c are glued to the boundaries contiguous to the edge 210, as represented in FIG. 3, in which glue beads 112 are represented. In FIG. 2, the glue 112 is distributed over the inner surface of the cut pieces 110a and 110c, so as to ensure a firm hold of the lining element 100 on the shell 200. Alternatively, a double-sided type adhesive strip may also be used.

[0075] Advantageously, a layer of foam 113 is disposed between the edge 210 and the central cut piece 110b. Optionally, the foam layer 113 is glued on the edge 210 and/or the inner surface of the central cut piece 110b. Preferably, the used glue is water-based glue.

[0076] The lining element 100 is obtained by a manufacturing method 300 which is described hereinafter, illustrated by the flowchart of FIG. 7.

[0077] During a flat cutting step 310, the cut pieces 110a, 110b and 110c are obtained by flat cutting a flexible and planar, or flattened, material, such as a drape of a flexible material or a sheet of a flexible material.

[0078] Of course, the cut piece may be optimized so as to minimize unusable material scraps, for example by using cutting optimization software during the phase of programming a cutting controller.

[0079] Optionally, during a step 320 of forming a hem, a hem is formed over the longitudinal boundary of a cut piece, in accordance with what has been disclosed so far.

[0080] Optionally, during a reinforcement step 330, a reinforcement is fastened on an inner surface of a cut piece. For example, fastening of the reinforcement may be done by gluing.

[0081] The reinforcement step 330 is represented subsequent to step 320 of forming a hem in FIG. 7, nonetheless these steps can also be indifferently reversed.

[0082] During an assembly step 340, the cut pieces 110a, 110b and 110c are secured together, preferably by sewing. The assembly is performed at the longitudinal boundaries of the cut pieces 110a, 110b and 110c, which are bound to one another.

[0083] Of course, the manufacturing method 300 can be generalized to any other number of cut pieces.

[0084] Moreover, a method 400 for setting up a lining element 100 over an aeronautical seat shell 200 is also described hereinafter, illustrated by the flowchart of FIG. 8.

[0085] During a preparation step 410, a bonding means is applied over the boundaries contiguous to the edge 210 of the shell 200. According to one variant, a double-sided adhesive tape is placed over the boundaries contiguous to the edge 210, whereas according to another variant, a masking adhesive tape is placed over the boundaries contiguous to the edge 210, so as to enable a proper application of a glue bead 112 over said contiguous boundaries.

[0086] Optionally, during a step 415 of setting up a foam, the foam 113 is set up over the edge 210. Preferably, the foam is set up using a holding tool in which foam sections are placed, and by which a substantially uniform pressure can be applied. In this manner, an even set-up of the foam 113 can be ensured.

[0087] During a set-up step 420, the lining element 100 is set up over the edge 210 (covered with foam 113 or not). Preferably, the lining element 100 is set up starting from a substantially curved portion of the edge 210. During the set-up step 420, in particular the lateral cut pieces 110a and 110c are smoothed on the boundaries contiguous to the edge 210, so as to obtain an aesthetically-pleasant transition between a cut piece and the shell 200. Preferably, the lining element 100 is held in position by a suitable tool (by clamping, under a weight, etc.) until the glue 112 cures.