Support plate for aircraft seat unit

Description

[0001] The present invention relates to a support pallet for an aircraft seat unit. The invention finds a particularly advantageous, but not exclusive, application with business class aircraft seat units. By "seat unit" is meant the seat as such, as well as all elements associated with the seat, for example an armrest, a console, a privacy shell, or the like.

[0002] A seat unit support pallet is an interface part providing a mechanical connection between the aircraft rails and at least one element of the seat unit, such as the seat structure.

[0003] As shown in the figure 1 , a support pallet 1 for an aircraft seat unit comprises, in a manner known per se, a reinforcement panel 2 as well as a front cross member 3 and a rear cross member 4 located on either side of the reinforcement panel 2. The cross members 3 and 4 are generally constituted by beams.

[0004] The assembly of this assembly is carried out by means of two side members 5, 6 each provided with a groove 8 receiving an edge of the reinforcement panel 2. The fixing between each side member 5, 6 and the panel 2 is carried out for example by riveting. In addition, a side member 5, 6 has at each of its ends a housing 9 for receiving respectively the front cross member 3 and the rear cross member 4. The fixing of the cross members 3, 4 to the side members 5, 6 is carried out for example by means of bolts or any other suitable fixing device.

[0005] The support pallet 1 further comprises fixing means 11 with the seat and an associated privacy shell. The pallet 1 is also equipped with fixing means with locks 12 ensuring the mechanical connection between the pallet 1 and the rails extending along the floor of the aircraft cabin.

[0006] However, such a configuration is cumbersome, particularly in height, given the significant thickness of the crosspieces 3, 4. Furthermore, the use of elements made of different materials (the panel 2 is made of a composite material while the crosspieces 3, 4 and the side members 5, 6 are made of different metallic materials) requires adapting the fixing interfaces with the different components, which makes the assembly of the assembly complex. It should also be noted that the assembly of the locks 12 is fixed due to their positioning on two crosspieces 3, 4 parallel to each other. Such an arrangement therefore limits the possibility of integrating components under the aircraft seat.

[0007] Document US2015115101 describes a ground connection assembly for mechanically connecting an aircraft seat to a floor structure of an aircraft. The ground connection assembly can be fixed on at least three fixing points with a respective fixing element to the floor structure.

[0008] US2017 / 274999 describes an extendable connecting member for attaching a passenger seat to a cabin floor or support structure. Ribs may be provided on either side of a seat leg attached to the connecting member.

[0009] Document US5868472 describes an aircraft seat frame comprising a seat back portion having a pair of side rails attached to a seat structural portion so as to transfer a load thereto. Ribs may be provided in particular on either side of structural elements forming the seat back portion.

[0010] US2015202992 describes a base frame assembly for a passenger seat comprising a main frame with a seat support structure and a side support structure. The side support structure comprises two seat fittings and the seat support structure comprises a seat connector and a secondary frame pivotally coupled to the main frame. A passenger seat and a surrounding monument are mounted on the base frame assembly.

[0011] Document US7857259 describes a modular seating system for a passenger compartment of a vehicle, in particular an aircraft, with at least one seat which comprises a seat unit with a seating element and a seat back, a seat frame with at least one pair of essentially vertical support elements, at the upper end of which is arranged a supporting structure on which the seat unit rests and a fastening structure in the floor of the passenger compartment with at least two longitudinal rails, which have a predetermined spacing to each other, for receiving the lower ends of the seat unit.

[0012] US2018327097 describes a fastening device for a component that can be secured to rails of a floor structure of an aircraft interior comprising at least two adapter plates. The adapter plates are decoupled from each other and configured to be secured to the rails. The adapter plates are configured to secure the component having mutually spaced fastening fasteners.

[0013] Documents US2012 / 235453A1 and CA2626278A1 each describe a seat comprising a support pallet comprising stiffening ribs arranged on one (lower) face, the other face being smooth.

[0014] The invention aims to effectively remedy at least one of the aforementioned drawbacks by providing a support pallet for an aircraft seat unit according to claim 1. Preferred embodiments are defined in the dependent claims.

[0015] Generally speaking, the support pallet includes: a body comprising an upper face and a lower face, lock fixing means each provided in a portion of the body, the lock fixing means each providing a fixing between the body and a seat rail lock or with an intermediate connecting piece establishing a connection between the body and a lock, seat unit fixing means each provided in a portion of the body, the seat unit fixing means each providing a fixing between the body and an element of the seat unit, the portions of the body comprising the lock fixing means and the portions of the body comprising the seat unit fixing means, as well as the remainder of the body constituting a single, single-piece part, the support pallet further comprising stiffening ribs arranged on the lower face of its body, the upper face of the body being smooth.

[0016] The support pallet of the invention is distinguished by the following characteristics: the stiffening ribs extend along stress paths between the lock attachment means appearing during a dynamic mechanical strength test consisting of deformation of the aircraft floor while the support pallet is mounted on rails and during which a stress is imparted to one of the rails so as to cause it to descend by an angle of 10 degrees downwards and another stress is imparted to the other rail so as to cause it to pivot by an angle of 10 degrees.

[0017] The invention thus makes it possible to produce a support pallet for a seat unit of low thickness that is more compact than a support pallet according to the state of the art. In addition, due to the elimination of the beams, the invention provides great freedom in positioning the lock fixing means, which frees up space under the seat. The production of the support pallet in a single piece, which is therefore made of a single material, also facilitates the interfaces of the support pallet with the various components of the seat unit.

[0018] According to one embodiment, said support pallet further comprises stiffening ribs.

[0019] According to one embodiment, the stiffening ribs extend along force paths between the lock fixing means appearing during a dynamic mechanical resistance test.

[0020] According to one embodiment, the stiffening ribs are arranged on the lower face of the body of the support pallet.

[0021] According to one embodiment, said support pallet comprises three lock fixing means.

[0022] According to one embodiment, said support pallet comprises a first lock fixing means and a second lock fixing means located on a first side of the body and a third lock fixing means located on a second side of the body.

[0023] According to one embodiment, the third lock fixing means is offset longitudinally with respect to a first straight line perpendicular to a longitudinal direction passing through the first lock fixing means and with respect to a second straight line perpendicular to a longitudinal direction passing through the second lock fixing means, so that the third lock fixing means is located longitudinally between the first lock fixing means and the second lock fixing means.

[0024] According to one embodiment, at least one through-hole is provided in the body.

[0025] According to one embodiment, the upper face of the body is smooth.

[0026] According to one embodiment, the upper face of the body comprises indexing zones to facilitate the positioning of an element of the seat unit relative to the seat unit fixing means.

[0027] According to one embodiment, the single piece is made of a metallic material, particularly aluminum.

[0028] The invention also relates to an assembly comprising at least one seat unit and a support pallet for the seat unit as defined above.

[0029] The invention further relates to an aircraft comprising an assembly as previously defined.

[0030] The present invention will be better understood and other characteristics and advantages will become apparent upon reading the detailed description which follows, comprising embodiments given for illustrative purposes with reference to the appended figures, presented as non-limiting examples, which may serve to complete the understanding of the present invention and the description of its embodiment and, where appropriate, contribute to its definition, in which: [ Fig. 1 ] There figure 1 , already described, is a perspective view of a support pallet for a seat unit according to the state of the art; [ Fig. 2 ] There figure 2 is a perspective view of a seat unit mounted on a support pallet according to the present invention; [ Fig. 3] [Fig. 4 ] There figure 3 and the figure 4 are perspective views from different angles of the seat unit and support pallet according to the present invention; [ Fig. 5 ] There figure 5 is a bottom view of the seat unit and support pallet according to the present invention; [ Fig. 6a ] There figure 6a is a perspective view of the support pallet for a seat unit according to the present invention; [ Fig. 6b ] There figure 6b is a bottom view of the support pallet for a seat unit according to the present invention; [ Fig. 7 ] There figure 7 is a map of the mechanical stresses undergone by the support pallet for the seat unit according to the invention during a dynamic stress test.

[0031] It should be noted that, in the figures, the structural and / or functional elements common to the different embodiments may have the same references. Thus, unless otherwise stated, such elements have identical structural, dimensional and material properties.

[0032] THE figures 2 , 3, et 4 show a seat unit 15 comprising a seat 16 associated with a removable armrest 17 and a console 18 provided with a shell 19. This set of elements is intended to be fixed on the rails 21.1, 21.2 of an aircraft by means of a seat unit support pallet 23. The seat 16 comprises in particular a seat 24 associated with a seat structure 25 as well as a backrest 27 movable relative to the seat 24. The seat 16 is fixed on the support pallet 23 by means of the seat structure 25.

[0033] More precisely, the support pallet 23 comprises a body 28 having an upper face 29.1 and a lower face 29.2.

[0034] As can be seen on the figures 3 et 4 , lock fixing means 31.1, 31.2, 31.3 are each provided in a portion 32 of the body 28. The lock fixing means 31.1, 31.2, 31.3 each provide fixing with an intermediate connecting piece 34 shown in the figure 6a establishing a connection between the body 28 and a lock. In this case, the lock fixing means 31.1, 31.2, 31.3 are constituted by openings allowing the fixing of the intermediate connecting piece 34. Alternatively, the lock fixing means 31.1, 31.2, 31.3 make it possible to ensure direct fixing between the body 28 and a corresponding seat rail lock.

[0035] Furthermore, seat unit fixing means 36 are each provided in a portion 37 of the body 28. The seat unit fixing means 36 make it possible to ensure fixing between the body 28 and an element of the seat unit 15. In this case, the seat unit fixing means 36 are each constituted by a threaded opening provided in the upper face 29.1 of the body 28. A threaded opening is intended to receive a fixing member, such as a screw, ensuring fixing between an element of the seat unit 15 and the support pallet 23. The element of the seat unit 15 to be fixed to the body 28 may be the seat 16 as such via the seat structure 25, or any element arranged around the seat 16, such as for example the armrest 17 and / or the console 18 and / or the shell 19. It will also be possible to fix an electronic box on the support pallet 23.

[0036] The portions 32 of the body 28 of the support pallet 23 comprising the lock fixing means 31.1, 31.2, 31.3 and the portions 37 of the body 28 of the support pallet 23 comprising the seat unit fixing means 36 as well as the remainder of the body 28 of the support pallet 28 constitute a single, single-piece part, as is clearly evident from the figures 6a And 6b .

[0037] In other words, there is a continuity of material between the portions 32 of the body 28 of the pallet comprising the lock fixing means 31.1, 31.2, 31.3, the portions 37 of the body 28 of the pallet comprising the seat unit fixing means 36, and the rest of the body 28 extending between these different portions 32, 37.

[0038] The single, one-piece part constituting the support pallet 23 is preferably made of a metallic material, in particular aluminum. Alternatively, the part could be made of another metallic material, for example steel or magnesium. The single-piece part is preferably made by solid machining or by 3D printing.

[0039] According to the invention, the upper face 29.1 of the body 28 is smooth, while stiffening ribs 39 are arranged on the lower face 29.2 of the body 28 of the support pallet 23.

[0040] There figure 7 shows a distribution of the forces undergone by the support pallet 23 during a dynamic mechanical resistance test. This mechanical resistance test consists of a deformation of the floor of the aircraft while the support pallet 23 is mounted on the rails 21.1, 21.2. During this so-called "pitch and roll" type test, a stress is imparted to one of the rails 21.1, 21.2 so as to make it descend by a given angle, for example of the order of 10 degrees downwards, and another stress is imparted to the other rail 21.1, 21.2 so as to make it pivot by a given angle, for example of the order of 10 degrees.

[0041] According to the invention, the stiffening ribs 39 extend along force paths between the lock fixing means 31.1, 31.2, 31.3 appearing in zone Z during the mechanical strength test.

[0042] Advantageously, the support pallet 23 is of the "three fixing point" type, that is to say that it comprises three lock fixing means 31.1, 31.2, 31.3.

[0043] A first latch attachment means 31.1 and a second latch attachment means 31.2 are located on a first side of the body 28. The latch attachment means 31.1 and 31.2 are longitudinally aligned with each other. By "longitudinally aligned" is meant that the first latch attachment means 31.1 and the second latch attachment means 31.2 are both located on the same straight line along which a rail 21.1, 21.2 extends.

[0044] "Longitudinal direction" means the direction of elongation of the rails 21.1, 21.2 of the aircraft or a direction parallel to the direction of elongation of the rails 21.1, 21.2 of the aircraft. The first and second fixing means 31.1, 31.2 each carry a lock intended to cooperate with the first rail 21.1.

[0045] A third lock fixing means 31.3 is located on a second side of the body 28 opposite the first side carrying the first and second fixing means 31.1, 31.2. The third lock fixing means 31.3 carries a lock intended to cooperate with the second rail 21.2.

[0046] As can be seen on the figures 5 And 6b , the third lock fixing means 31.3 is offset longitudinally with respect to a first straight line D1 perpendicular to a longitudinal direction passing through the first lock fixing means 31.1 (cf. offset L1) and with respect to a second straight line D2 perpendicular to a longitudinal direction passing through the second lock fixing means 31.2 (cf. offset L2), so that the third lock fixing means 31.3 is located longitudinally between the first lock fixing means 31.1 and the second lock fixing means 31.2.

[0047] The third lock attachment means 31.3 is not aligned with the first lock attachment means 31.1 and the second lock attachment means 31.2.

[0048] As can be seen on the figures 6a And 6b , at least one through recess 40 is provided in the body 28 of the pallet. This recess 40 is made in an area of ​​the body 28 subjected to low stresses during the dynamic test. This recess 40 makes it possible to reduce the weight of the support pallet 23. If necessary, this recess 40 may allow the passage of electrical wires from an electrical harness of the aircraft and intended to be connected to an electrical box arranged near the seat. The electrical box may be fixed on the upper face 29.1 of the body 28.

[0049] According to certain embodiments, the upper face 29.1 of the body 28 of the support pallet 23 comprises indexing zones 42 to facilitate the positioning of an element of the seat unit 15 relative to the seat unit fixing means 36, as illustrated by the figure 6b .

[0050] These indexing zones 42 may consist, for example, of hollows made in the upper face 29.1 to guide the element of the seat unit 15, so that the fixing holes of the element of the seat unit 15 are located opposite the tapped holes of the means 36. Alternatively, the indexing zones 42 may be constituted by guide walls originating from the upper face 29.1 of the body 28.

[0051] Alternatively, the support pallet 23 may have more than three fixing points, in particular four or more fixing points.

[0052] Alternatively, the fixing means 31.1, 31.2, 31.3, 36 consist of projecting portions of the body 28 of the support pallet 23.

[0053] Of course, the different characteristics, variants and / or embodiments of the present invention can be associated with each other in various combinations to the extent that they are not incompatible or exclusive of each other.

[0054] Obviously, the invention is not limited to the embodiments described above and provided solely by way of example, but only by the appended claims.

Claims

1. A support pallet (23) for an aircraft seat unit (15), comprising: - a body (28) comprising an upper face (29.1) and a lower face (29.2), - lock fixing means (31.1, 31.2, 31.3), each of them being provided in a portion (32) of the body (28), each of the lock fixing means (31.1, 31.2, 31.3) enabling to fixing the body (28) and a seat rail lock to one another or with the help of an intermediate connecting piece (34) for fixing the body (28) and a lock to one another, - seat unit fixing means (36), each of them being provided in a portion (37) of the body (28), each of the seat unit fixing means (36) enabling to fix the body (28) and an element of the seat unit (15) to one another, - the portions (32) of the body (28) comprising the lock fixing means (31.1, 31.2, 31.3) and the portions (37) of the body (28) comprising the seat unit fixing means (36), as well as the remainder of the body (28) forming a single monobloc part, - said support pallet further comprising stiffening ribs (39) on the lower face (29.2) of the body (28), - the upper face (29.1) of the body (28) being smooth, characterized in that - the stiffening ribs (39) extend along stress paths between the lock fixing means (31.1, 31.2, 31.3) appearing during a dynamic mechanical resistance test consisting of a deformation of the aircraft floor while the support pallet (23) is mounted on rails (21.1, 21.2) and during which a stress is imparted to one of the rails (21.1, 21.2) so as to make it descend by an angle of 10 degrees downwards and another stress is imparted to the other rail (21.1, 21.2) so as to make it pivot by an angle of 10 degrees.

2. The support pallet according to claim 1, characterized in that it comprises three lock fixing means (31.1, 31.2, 31.3).

3. The support pallet according to claim 2, characterized in that it comprises a first lock fixing means (31.1) and a second lock fixing means (31.2) on a first side of the body (28) and a third lock fixing means (31.3) on a second side of the body (28).

4. The support pallet according to claim 3, characterized in that the third lock fixing means (31.3) is longitudinally offset with respect to a first straight line (D1) perpendicular to a longitudinal direction through the first lock fixing means (31.1) and with respect to a second straight line (D2) perpendicular to a longitudinal direction through the second lock fixing means (31.2), so that the third lock fixing means (31.3) is located longitudinally between the first lock fixing means (31.1) and the second lock fixing means (31.2).

5. The support pallet according to any of the claims 1 to 4, characterized in that at least one through recess (40) is provided in the body (28).

6. The support pallet according to any of the claims 1 to 5, characterized in that the upper face (29.1) of the body (28) comprises indexing zones (42) for facilitating the positioning of an element of the seat unit relative to the seat unit fixing means (36).

7. The support pallet according to any of the claims 1 to 6, characterized in that the single monobloc part is made of a metallic material, in particular aluminum.

8. An assembly comprising at least one seat unit (15) and a support pallet (23) for a seat unit as defined according to any of the preceding claims.

9. An aircraft comprising an assembly as defined according to the preceding claim.