Seat unit provided with a lower tubular seat structure

Abstract

The invention relates to a seat unit (20), in particular for an aircraft cabin, comprising: - a seat (21) provided with a seat cushion and a backrest movement device (29), and - a seat base structure (25) on which the seat (21) is mounted, the seat base structure (25) comprising a frame (41) having a tubular structure, the frame comprising: - a first lower tube (43) and a second lower tube (44), each carrying at least one bolt (38) to fasten on a rail (26), and - two fastening legs (45) for fastening the seat cushion and backrest movement device (29), a fastening leg (45) being formed by a tube connected at one end to the first lower tube (43) of the frame (41) and at the other end to the second lower tube (44) of the frame (41).

Description

Technical Field

[0001] This invention relates to a seat unit with a lower tubular seat structure. The invention is particularly advantageous, but not exclusively, for use in "business class" type aircraft seat units. "Seat unit" refers to the seat itself, as well as all components associated with the seat, such as privacy covers, the lower seat structure, and (where applicable) armrests, consoles, or other components. Background Technology

[0002] The lower seat unit structure is an interface component that provides a mechanical connection between the aircraft's rails and at least one component of the seat (such as the seating portion and the backrest movement device).

[0003] like Figure 1 As shown, the lower seat structure 1 described in document EP18159172 is known to include a reinforcing panel 2 and a front transverse member 3 and a rear transverse member 4 located on either side of the reinforcing panel 2. The transverse members 3 and 4 are typically constructed of beams.

[0004] The assembly is installed via two spars 5 and 6, each spar having a groove for receiving the edge of the reinforcing panel 2. The spars 5 and 6 are fixed to the panel 2, for example, by rivets, and the spars 5 and 6 are mounted to the spars 3 and 4 by screws.

[0005] The lower structure 1 also includes legs 7 for fixing to the seating portion and backrest movement device, and brackets 8 for allowing the privacy cover to be fixed on its upper surface.

[0006] The lower structure 1 is also equipped with a lock 9 supported by transverse members 3 and 4. The lock 9 ensures the mechanical connection between the lower seat structure 1 and the guide rails extending along the floor of the aircraft cabin. The installation of the wing spars, the installation of the guide rail fasteners, and the mounting of the housing onto the beams are accomplished by screws.

[0007] Alternatively, such as Figure 2 As shown, the lower seat structure 1 described in document FR1912243 includes a machined base 11 with a lock 9 on its underside to provide a mechanical connection between the lower structure 1 and the guide rails of the aircraft cabin. The lower structure 1 also includes legs 7 on its upper surface for securing to the seating portion and backrest movement device, as well as brackets 8 that allow the privacy canopy to be secured.

[0008] The lower seat structure can have a variety of possible configurations, which are particularly related to the angular adjustment of the seat relative to the cabin axis, the specific platform of the aircraft, and the specific requirements of the airline. This involves various interface components for installing these locks and securing these brackets.

[0009] This significant increase in interface components has resulted in complex designs, additional weight, and the risk of installation errors and substantial installation time.

[0010] Furthermore, since the tolerances depend on the dimensions of the mechanical installation, the tolerances of the mechanical installation increase with the number of interface components.

[0011] The installation of numerous components also limits the space available for mounting the electrical box, which supplies power to various electrical components of the seat unit via a set of electrical wiring harnesses, such as seat actuators or video screens of IFE (In-Flight Entertainment) type entertainment systems.

[0012] Furthermore, with increasingly stringent new regulations in place, known substructures are beginning to reach their limits in terms of resisting mechanical forces during impact. Summary of the Invention

[0013] The present invention aims to effectively overcome the above-mentioned deficiencies by proposing a seat unit, particularly for use in aircraft cabins, the seat unit comprising:

[0014] - A seat, the seat being provided with a seating portion and a backrest movement device, and

[0015] - Lower seat structure, the seat is mounted on the lower seat structure.

[0016] -The lower seat structure includes a tubular structural frame, the frame comprising:

[0017] - A first lower tube and a second lower tube, each carrying at least one lock to secure it to the guide rail, and

[0018] - Two fixed legs for the seating portion and backrest movement mechanism, the fixed legs being formed of tubes, one end of which is connected to the first lower tube of the frame and the other end of which is connected to the second lower tube of the frame.

[0019] Therefore, due to the tubular structure of the substructure, the present invention can provide greater design flexibility and a greater degree of modularity to the substructure by allowing the fasteners to move according to the position of the guide rail in the aircraft cabin without the need to create new interface components.

[0020] The tubular design of the components also allows for control over the torsional zones during a collision, improving the behavior of structures subjected to high mechanical stresses. In fact, while maintaining good stiffness in the collision-related directions, the tubular structure produces flexibility, allowing the structure to deform in response to the deformation of the aircraft cabin floor.

[0021] The tubular structure can be fabricated on a welding template, and tolerances can be better managed by eliminating the dispersion of clearances caused by screw mounting. Compared to known lower seat structures, this invention also allows for weight reduction. This invention also frees up space under the seat, which facilitates the integration of the electrical box.

[0022] Furthermore, this invention makes it easier to disassemble the frame during maintenance operations to access the faulty electrical box located beneath the seat. It should also be noted that by integrating the fixed support legs into the lower seat structure, this invention facilitates the mounting of the seating portion and backrest movement mechanism onto the frame.

[0023] According to one embodiment of the invention, the fixed leg protrudes relative to the plane in which the first lower tube and the second lower tube of the frame extend.

[0024] According to one embodiment of the present invention, a fixing guide is arranged on the upper portion of the corresponding fixing leg.

[0025] According to one embodiment of the invention, the first lower tube and the second lower tube are curved such that the gap between the first lower tube and the second lower tube is variable when moving from one end of the tube to the other.

[0026] According to one embodiment, the seat unit further includes a privacy shroud.

[0027] According to one embodiment of the present invention, the lower seat structure further includes a reinforcing band formed of a plurality of tubes, and at least a portion of the privacy cover is fixed to the reinforcing band.

[0028] According to one embodiment of the invention, the reinforcing band is surrounded by a portion of the privacy shell.

[0029] According to one embodiment of the invention, the height of the vertical extension of the reinforcing strip is between 12cm and 50cm, and preferably about 38cm.

[0030] According to one embodiment of the invention, the privacy cover includes a lower portion and an upper portion, so that only the lower portion can be removed to access the electrical box under the seat.

[0031] According to one embodiment of the invention, at least one through-slot for an electrical wiring harness is fixed to a reinforcing strip.

[0032] According to one embodiment of the invention, the seat unit includes three locks to form a configuration with three fixing points.

[0033] According to one embodiment of the present invention, the lock is associated with a lock support.

[0034] According to one embodiment of the invention, the lock support includes a single opening through which the lower tube passes, allowing the lock support to move along the lower tube before being secured by welding it to a position corresponding to the positioning of the guide rail.

[0035] According to one embodiment of the invention, the lock support includes two openings for passage of a first lower tube and a second lower tube, respectively, so as to allow the lock support to move along the lower tube before being fixed by welding the lock support to a position corresponding to the positioning of the guide rail.

[0036] According to one embodiment of the present invention, the lock support is made of two parts.

[0037] The present invention also relates to an aircraft comprising a plurality of seat units as described above. Attached Figure Description

[0038] The invention will be better understood by reading the following detailed description, and other features and advantages will become apparent. The detailed description includes embodiments presented by way of non-limiting example with reference to the accompanying drawings, which are given for illustrative purposes and can be used to complete the understanding of the invention and its embodiments and ultimately contribute to its definition, wherein:

[0039] [ Figure 1 Description Figure 1 This is a perspective view of a lower seat structure of the first type based on existing technology;

[0040] [ Figure 2 Description Figure 2 This is a perspective view of a second type of lower seat structure based on existing technology;

[0041] [ Figure 3a ][ Figure 3b ] Figure 3a and Figure 3b These are perspective views of the seat unit according to the present invention before and after the seat is installed in the lower seat structure;

[0042] [ Figure 4a ][ Figure 4b ] Figure 4a and Figure 4b These are perspective views of the lower portion of the seat unit according to the present invention before and after the seat is installed in the lower seat structure;

[0043] [ Figure 5 ] Figure 5 This is a perspective view of the lower seat structure according to the present invention;

[0044] [ Figure 6 ] Figure 6This is a perspective view of the lower seat structure according to the present invention and the electrical box associated with the electrical wiring harness of the electrical components to be connected to the seat unit;

[0045] [ Figure 7 ] Figure 7 This is a perspective view of the electrical wiring harness through-slot on the reinforcing strip of the lower seat structure according to the present invention;

[0046] [ Figure 8a ] Figure 8a It is a 3D view of the two parts of the privacy cover in an assembled state;

[0047] [ Figure 8b ] Figure 8b This is a perspective view showing the possibility of removing the lower part of the privacy cover to access the electrical box under the seat;

[0048] [ Figure 9 ] Figure 9 This is a perspective view from below, showing the attachment system used to attach the privacy shroud to the lower seat structure;

[0049] [ Figure 10 ] Figure 10 This is a detailed perspective view of the attachment system used to attach the privacy cover to the lower seat structure;

[0050] [ Figure 11a ][ Figure 11b ] Figure 11a and Figure 11b These are longitudinal and transverse sectional views, respectively, of a first embodiment of the lock support member and related lock according to the present invention;

[0051] [ Figure 12a ][ Figure 12b ] Figure 12a and Figure 12b These are longitudinal and transverse sectional views, respectively, of a second embodiment of the lock support member and related lock according to the present invention;

[0052] [ Figure 13a ][ Figure 13b ] Figure 13a and Figure 13b These are longitudinal and transverse sectional views, respectively, of a third embodiment of the lock support and related lock according to the present invention;

[0053] [ Figure 14 ] Figure 14 This is a perspective view of a template used to manufacture the lower seat structure according to the present invention. Detailed Implementation

[0054] It should be noted that, Figure 3aIn the accompanying drawings and in the various embodiments, structural and / or functional elements common to the embodiments may have the same reference numerals. Therefore, unless otherwise stated, such elements have the same structural, dimensional, and material properties.

[0055] Figure 3a and Figure 3b The diagram shows a seat unit 20, particularly a seat unit for an aircraft cabin, which includes a seat 21, a privacy enclosure 22 extending around the seat 21 to isolate the passenger from the external environment, a console 23, armrests 24, and a lower seat structure 25 for securing components to the aircraft cabin via rails 26.

[0056] More specifically, seat 21 includes a seating portion 28 and a reclining backrest 31. Seat 21 is preferably a "business" type seat movable between a seating position and a bed position, in which the various components of seat 21 extend along a generally horizontal plane. Figure 4a and Figure 4b The visible seating portion and backrest movement device 29 includes mechanical components that ensure movement of the seating portion 28 and backrest 31, particularly from the seat position to the bed position and vice versa.

[0057] The console 23 has an upper surface 32 on which passengers can place objects, such as... Figure 3a and Figure 3b As shown. The console 23 may include a removable dining tray 33, a storage unit 34, and a power outlet 35 for charging electronic devices. The console 23 may also include an internal foot housing 36, which... Figure 8b It is clearly visible that it is used to receive the rear passenger's feet when the rear passenger's seat 21 is in the bed position.

[0058] The seating section and backrest movement device 29, privacy cover 22 and console 23 are mounted on the lower seat structure 25, which is fixed to the aircraft cabin rail 26 by lock 38.

[0059] like Figure 3a and Figure 6 As can be seen, electrical boxes 39 are located below seat 21. These electrical boxes 39 are used to power various electrical components of seat unit 20 via a set of electrical wiring harnesses 40, such as seat actuators 21 or video screens of IFE (IFE = In-Flight Entertainment) type entertainment systems.

[0060] Advantageously, such as Figure 5 and Figure 6As can be seen, the lower seat structure 25 includes a frame 41 with a tubular structure. "Frame with a tubular structure" means frame 41 formed by a plurality of hollow tubes. Preferably, the tubular structure is a "mechanically welded" type structure, that is, a structure formed by hollow metal tubes welded together. Advantageously, the metal tubes are made of steel. Alternatively, however, the tubes can be made of another metallic material, such as aluminum or magnesium, or any other material suitable for the application. The tubes preferably have a circular or elliptical cross-section, which is particularly suitable for withstanding the torsional forces associated with the deformation of the aircraft cabin floor during a collision. Alternatively, however, the tubes can have rectangular, square, trapezoidal, triangular cross-sections, or any other shape suitable for the application.

[0061] The cross-section can be constant or variable along the length of the tube to locally reinforce areas of the structure subjected to particularly high mechanical stresses by welding or butt joint reinforcements or by deforming the tube through a butt joint forming process. In fact, the tubular structure allows for the independent determination of material thickness relative to the inner diameter of the tube to accommodate the stiffness of the substructure.

[0062] In this configuration, frame 41 includes a first lower tube 43 and a second lower tube 44. Each of the first lower tube 43 and the second lower tube 44 carries at least one lock 38 for securing to the guide rail 26 in the aircraft cabin.

[0063] The frame 41 also includes a seating portion and two fixed legs 45 of the backrest movement device 29. The fixed legs 45 are formed of tubes, one end of which is connected to a first lower tube 43 of the frame 41 and the other end of which is connected to a second lower tube 44 of the frame 41.

[0064] like Figure 4a and Figure 4b As can be clearly seen, the fixed leg 45 protrudes relative to a plane P in which the first lower tube 43 and the second lower tube 44 of the frame 41 extend. The fixed leg 45 includes an upper portion 48 and two connecting portions 49. One connecting portion 49 mechanically connects one end of the upper portion 48 to a corresponding lower tube 43, 44.

[0065] The seating portion and backrest movement device 29 are designed to be secured to a fixed guide 51. The fixed guide 51 is arranged on the upper portion 48 of the corresponding fixed support leg 45 for easy access by the operator. The fixed guide 51 also has an indexing function to facilitate the positioning of the seating portion and backrest movement device 29 during the installation of the seat 21.

[0066] The first lower tube 43 and the second lower tube 44 are bent such that the gap between the first lower tube 43 and the second lower tube 44 is variable when moving from one end of the tubes 43 and 44 to the other end, as shown below. Figure 5 and Figure 6 As shown. In this configuration, as the vehicle moves from one end of the fixed support leg 45 toward the opposite end, the gap between the two lower tubes 43 and 44 tends to decrease. This configuration optimizes the floor space of the lower seat structure 25.

[0067] The lower seat structure 25 also includes a reinforcing band 52 formed by a plurality of tubes 53, 54. The plurality of tubes 53, 54 of the reinforcing band 52 are mechanically connected to the lower tubes 43, 44. The reinforcing band 52 is surrounded by a portion of the privacy cover 22. At least a portion of the privacy cover 22 is secured to the reinforcing band 52.

[0068] The reinforcing band 52 can effectively absorb the force applied to the privacy cover 22 in the event of an impact. This improves the mechanical strength of the privacy cover 22 during a collision. In addition, since the cover 22 and the seat 21 are separately fixed to the lower seat structure 25, this configuration can distribute and divide the path of the force applied to the seat unit 20 during a collision.

[0069] More specifically, in the example shown, the reinforcing strip 52 includes uprights 53 and connecting pipes 54 that connect the uprights 53 to each other. For this purpose, one end of the upright 53 is connected to one of the lower pipes 43, 44, and the other end is connected to the connecting pipe 54. The connecting pipe 54 extends in a generally horizontal plane. Two adjacent uprights 53 can be connected together using additional reinforcing pipes. Alternative configurations of the pipes 53, 54 are, of course, possible.

[0070] Advantageously, the height of the vertical extension of the reinforcing strip 52 is between 12 cm and 50 cm, and preferably about 38 cm. "About" means a variation of plus or minus 10% around the target value.

[0071] like Figure 8a and Figure 8b As shown, the privacy cover 22 is preferably made of two parts. Thus, the privacy cover 22 includes a lower part 22.1 and an upper part 22.2, so that only the lower part 22.1 can be removed to access the electrical box 39 under the seat 21.

[0072] like Figure 9 and Figure 10 As can be seen, the privacy cover 22 can be secured to the reinforcing band 52 by means of a sleeve 55 fixed to the connecting tube 54. A securing member (such as a screw) is inserted into the sleeve 55 to engage with the threads in the interface portion of the cover 22. Alternatively, the screw can be replaced with a rivet, stud, or any other fastener suitable for this application.

[0073] The reinforcing band 52 can extend through the tubular portion 56 fixed to the console 23. In this case, the tubular portion 56 has a triangular shape corresponding to the shape of the console 23.

[0074] Preferably, at least one through-slot 57 for the electrical wiring harness 40 is fixed to the reinforcing strip 52, such as Figure 6 and Figure 7 As shown. For this purpose, the through-slot 57 preferably includes a removable fastening device 58 to allow the operator to easily secure the through-slot 57 to the tubes 53, 54 of the reinforcing strip 52. The removable fastening device 58 may be, for example, a resiliently deformable snap-fit ​​fastening device (e.g., a C-shaped snap-fit ​​fastening device).

[0075] Electrical harnesses 40 from electrical box 39 that connect to the various electrical components of seat 21 can therefore be arranged in through slots 57 so that they can be installed in the lower part of seat 21.

[0076] The seat unit 20 preferably includes three locks 38 to have a configuration with three fixing points. However, alternatively, the seat unit 20 may have more than three locks 38.

[0077] like Figure 11a , Figure 11b , Figure 12a , Figure 12b , Figure 13a and Figure 13b As can be seen, lock 38 is associated with lock support 59. Lock 38 is mounted to rotate about a horizontal axis relative to lock support 59, thereby aiding in its positioning on the corresponding guide rail 26 due to its rotational degree of freedom. In this configuration, the pivot axis of lock 38 extends longitudinally relative to the longitudinal axis of the aircraft.

[0078] The lock support 59 may include a single opening 60 through which the lower tubes 43, 44 pass, so as to allow the lock support 59 to move along the lower tubes 43, 44 before it is fixed by welding the lock support 59 to a position corresponding to the positioning of the guide rail 26.

[0079] Alternatively, Figure 5 The right-side lock support 59 includes two openings 60, 60' for the passage of the first lower tube 43 and the second lower tube 44, respectively, to allow the lock support 59 to move along the lower tubes 43, 44 before it is secured by welding it to a position corresponding to the positioning of the guide rail 26. In this configuration, the pivot axis of the lock 38 extends in a direction transverse to the longitudinal axis of the aircraft.

[0080] exist Figure 12a and Figure 12b In one embodiment, the lock support 59 is made of two parts.

[0081] exist Figure 13a and Figure 13bIn one embodiment, the lock support 59 is fixed to the corresponding lower tubes 43 and 44 by a pin 61 passing through the corresponding lower tubes 43 and 44.

[0082] Figure 14 The template 63 shown is used to realize the lower seat structure 25 according to the invention. The various tubes 43, 44, 53, 54 of the frame 41 and reinforcing strap 52 are held in place with the aid of clamps 64 supported by the columns 65 of the template 63. Locking supports 38 move along the lower tubes 43, 44 to engage with corresponding guide rails 26 at positions corresponding to specific cabin configurations. A plate 66 may define the gap between the fixed legs 45 of the seat 21.

[0083] Once all components of the lower seat structure 25 are in the desired positions, the operator or robot can ensure that tubes 43, 44, 53, and 54 are welded together and that the locking support 38 is welded to the lower tubes 43 and 44. This completes the lower seat structure 25. Template 63 thus allows for a high degree of modularity in the lower seat structure 25, making it easily adaptable to the construction of the aircraft cabin, seat 21, console 23, and the positioning of the rails 26.

[0084] When the seat unit 20 is installed inside the aircraft cabin, the lower seat structure 25, associated with the privacy shroud 22 and the console 23, is first mounted on the rail 26 via a lock 38, as... Figure 3a and Figure 4a As shown.

[0085] Then, as Figure 3b and 4b As shown, the seating portion and backrest movement device 29 are positioned on the fixing guide 51, which ensures the position of the seating portion and backrest movement device 29 is rotated. Once the seating portion and backrest movement device 29 are in the correct position relative to the privacy cover 22, the seating portion and backrest movement device 29 are secured to the fixing guide 51 by means of suitable fasteners (such as screws or rivets).

[0086] In the example shown, seat 21 has an axis that forms a non-zero angle with respect to the longitudinal axis of the aircraft. Alternatively, the axis of seat 21 may extend parallel to the longitudinal axis of the aircraft.

[0087] Alternatively, seat 21 may have multiple positions. Alternatively, multiple seats 21 may be mounted on the same lower seat structure 25.

[0088] The present invention also relates to an aircraft comprising a plurality of seat units 20 as described above.

[0089] Of course, different features, variations, and / or embodiments of the present invention can be associated with each other in various combinations, as long as they are compatible with each other or do not exclude each other. Furthermore, the present invention is not limited to the embodiments described above and is provided by way of example only. It includes various modifications, alternatives, and other variations that can be conceived by those skilled in the art in the context of the present invention, particularly any combination of the various modes of operation described above that can be employed individually or in combination.

Claims

1. A seat unit (20) for an aircraft cabin, the seat unit comprising: - Seat (21), the seat is provided with a seating portion and a backrest movement device (29), and - Lower seat structure (25), the seat (21) is mounted on the lower seat structure, The lower seat structure (25) is characterized in that it includes a frame (41) with a tubular structure, the frame comprising: - A first lower tube (43) and a second lower tube (44), each of the first lower tube (43) and the second lower tube (44) carrying at least one lock (38) for fixing to the guide rail (26), and - The two fixed legs (45) of the seating part and backrest movement device (29), each of the two fixed legs (45) is formed by a tube, one end of which is connected to the first lower tube (43) of the frame (41) and the other end of which is connected to the second lower tube (44) of the frame (41). -The seat unit further includes a privacy shroud (22). - The lower seat structure (25) further includes a reinforcing band (52) formed by a plurality of tubes (53, 54), at least a portion of the privacy cover (22) is fixed to the reinforcing band (52), and the plurality of tubes (53, 54) are connected to the first lower tube (43) and the second lower tube (44).

2. The seat unit according to claim 1, characterized in that, The fixed leg (45) protrudes relative to a plane (P) in which the first lower tube (43) and the second lower tube (44) of the frame (41) extend.

3. The seat unit according to claim 1 or 2, characterized in that, The fixed guide (51) is arranged on the upper part (48) of the corresponding fixed support leg (45).

4. The seat unit according to claim 1, characterized in that, The first lower tube (43) and the second lower tube (44) are curved such that the gap between the first lower tube (43) and the second lower tube (44) is variable when moving from one end of the first lower tube (43) to the other end.

5. The seat unit according to claim 1, characterized in that, The reinforcing band (52) is surrounded by a portion of the privacy cover (22).

6. The seat unit according to claim 1, characterized in that, The height (H) of the vertical extension of the reinforcing strip (52) is between 12 cm and 50 cm.

7. The seat unit according to claim 6, characterized in that, The height (H) is 38 cm.

8. The seat unit according to claim 1, characterized in that, The privacy cover (22) has a lower part (22.1) and an upper part (22.2), so that only the lower part (22.1) can be removed to access the electrical box (39) under the seat (21).

9. The seat unit according to claim 1, characterized in that, At least one through-slot (57) for the electrical wiring harness (40) is fixed to the reinforcing strip (52).

10. The seat unit according to claim 1, characterized in that, The seat unit includes three locks (38) in a configuration with three fixing points.

11. The seat unit according to claim 1, characterized in that, The lock (38) is associated with the lock support (59).

12. The seat unit according to claim 11, characterized in that, The lock support (59) has a single opening (60) through which the first lower tube (43) and the second lower tube (44) pass, so as to allow the lock support (59) to move along the first lower tube (43) and the second lower tube (44) before it is fixed by welding the lock support (59) to a position corresponding to the positioning of the guide rail (26).

13. The seat unit according to claim 11, characterized in that, The lock support (59) has two openings (60, 60') for the passage of the first lower tube (43) and the second lower tube (44), respectively, so as to allow the lock support (59) to move along the first lower tube (43) and the second lower tube (44) before it is fixed by welding the lock support (59) to a position corresponding to the positioning of the guide rail (26).

14. The seat unit according to claim 11, characterized in that, The lock support (59) is made of two parts.

15. An aircraft comprising a plurality of seat units (20) as described in any of the preceding claims.

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