Assembly comprising a wall and at least one beam provided with at least one attachment passing through the wall; central wing box of an aircraft comprising said assembly

Abstract

Assembly comprising a wall and at least one beam provided with at least one attachment passing through the wall, central wing box of aircraft comprising said assembly. The invention relates to an assembly comprising: at least one wall (54) having an inner face (Fint) and an outer face (Fext) opposite the inner face (Fint), at least one beam (52) positioned against the outer face (Fext) of the wall (54) and connected to the latter by connecting elements (56), at least one attachment (62) projecting from the inner face (Fint) of the wall (54) integral with the beam (52) and forming with the latter a single and the same piece made in one piece, the wall (54) comprising, for each attachment (62), a through hole (66) to allow the attachment (62) to pass through the wall (54).The invention also relates to an aircraft wing center box comprising at least one such assembly and to an aircraft comprising said wing center box. Figure 11.

Description

Title of the invention: Assembly comprising a wall and at least one beam provided with at least one attachment passing through the wall, central wing box of an aircraft comprising said assembly

[0001] The present application relates to an assembly comprising a wall and at least one beam provided with at least one attachment passing through the wall, to an aircraft wing center box comprising said assembly and to an aircraft comprising said wing center box.

[0002] According to an embodiment visible in [Fig.1], an aircraft comprises a fuselage 10 extending between a front tip 10.1 and a rear tip 10.2, wings 12 and a central wing box 14 connecting the wings 12 and the fuselage 10.

[0003] For the purposes of this application, a longitudinal direction is a direction parallel to a longitudinal axis, which is horizontal when the aircraft is on the ground, and extends between the forward and aft points 10.1, 10.2. A longitudinal plane is a vertical plane when the aircraft is on the ground and parallel to the longitudinal axis. A transverse plane is a plane perpendicular to the longitudinal axis.

[0004] The central wing box 14 comprises an upper panel 16, a lower panel 18, a forward spar 20, and a rear spar 22, the forward and rear spars 20, 22 being positioned in transverse planes offset along the longitudinal direction. The upper and lower panels 16, 18, as well as the forward and rear spars 20, 22, each have an inner face Fint oriented towards the interior of the central wing box 14, an outer face Fext opposite the inner face Fint, and stiffeners 24 positioned at the level of the inner face Fint.

[0005] According to an embodiment visible in figures 2 to 5, the central wing box 14 also includes at least one longitudinal beam 26 positioned against the external face Fext of the lower panel 18 and connected to the latter by connecting elements 28. According to one configuration, the longitudinal beam 26 includes a first web 26.1 as well as a first flange 26.2 pressed against the external face Fext of the lower panel 18.

[0006] In addition, the central wing box 14 includes at least one connecting rod 30 connected to the lower panel 18 by a fastener 32 positioned against the inner face Fint of the lower panel 18 and connected to the latter by connecting elements.

[0007] According to one embodiment, each fastener 32 comprises a second web 32.1 positioned in a longitudinal plane and second flanges 32.2, 32.2' positioned on either side of the second web 32.1. Thus, the fastener 32 has a T-shaped cross-section in transverse planes. The second flanges 32.2, 32.2' are attached against the inner face Fint of the lower panel 18 and connected to it by connecting elements.

[0008] According to one assembly method, the longitudinal beam 26 and the fastener 32 are positioned on either side of the lower panel 18 and connected to the latter by common connecting elements 28 which pass through the lower panel 18, the first and second flanges 26.2, 32.2, 32.2' of the longitudinal beam 26 as well as the fastener 32.

[0009] This embodiment is unsatisfactory due to the large number of parts to be assembled. These various parts must be adjusted, shimmed, and positioned relative to one another. For each connecting element 28, the stacked parts are drilled, and then the connecting elements are put in place. Consequently, the assembly of the three parts (lower panel 18, longitudinal beam 26, and fastener 32) is difficult to automate.

[0010] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0011] To this end, the invention relates to an assembly comprising: a. at least one wall having an inner face and an outer face opposite to the inner face, b. at least one beam positioned against the outer face of the wall and connected to it by connecting elements, c. at least one attachment protruding from the inner face of the wall.

[0012] According to the invention, the fastener is integral with the beam and forms with it a single, one-piece unit. In addition, the wall includes, for each fastener, a through hole to allow the fastener to pass through the wall.

[0013] This solution reduces the number of parts to be assembled, which simplifies the assembly process and potentially allows it to be automated.

[0014] According to another feature, the beam comprises at least a first web and at least a flange connected to the first web and attached to the external face of the wall, the attachment comprising a second web connected to the flange of the beam, the first and second webs being positioned on either side of the flange.

[0015] According to another feature, the first web of the beam has a first median plane. In addition, the second web of the fastener includes a second median plane, the first and second median planes being coplanar.

[0016] According to another feature, the assembly includes at least one seal interposed between, on the one hand, the wall and, on the other hand, the base and / or the second web of the beam, said seal being configured to ensure fluid tightness.

[0017] According to another feature, the through hole and the fastener are configured so as to delimit a small gap between the wall and the fastener.

[0018] According to another feature, the seal is configured to fill the gap between the wall and the fastener.

[0019] The invention also relates to a central wing box of an aircraft comprising at least one assembly according to one of the preceding characteristics.

[0020] According to one embodiment, the central wing box comprises: a. upper and lower panels as well as front and rear longitudinal members connected in pairs to form a box-section structure, each having an inner face and an outer face opposite to the inner face, b. at least one connecting rod having a first end connected to a first attachment fixed to a first beam attached against the outer face of the upper panel and a second end connected to a second attachment fixed to a second beam attached against the outer face of the lower panel.

[0021] The invention also relates to an aircraft comprising a central wing box according to one of the preceding characteristics.

[0022] Other features and advantages will become apparent from the following description of the invention, given by way of example only, with reference to the accompanying drawings, among which:

[0023] [Fig-1] is a perspective view of an aircraft,

[0024] [Fig.2] is a longitudinal section of a lower part of a central box of sail design illustrating a method of realizing a previous art,

[0025] [Fig.3] is a section of zone III of [Fig.2],

[0026] [Fig.4] is a top view of a fastener illustrating one embodiment of the art prior,

[0027] [Fig.5] is a longitudinal section of part of a central wing box illustrating an embodiment of the prior art,

[0028] [Fig.6] is a longitudinal section of a central wing box illustrating one embodiment of the invention,

[0029] [Fig.7] is a longitudinal section of a lower part of the central box of visible sail area in [Fig.6],

[0030] [Fig.8] is a view from below of a lower panel of the central wing box visible on the [Fig.6],

[0031] [Fig.9] is a section of zone IX of [Fig.7],

[0032] [Fig. 10] is a longitudinal section of part of a central wing box illustrating one embodiment of the invention, and

[0033] [Fig. 11] is a cross-section of part of a central wing box illustrating one embodiment of the invention.

[0034] According to an embodiment visible in [Fig. 6], a central wing box 40 The wing structure of an aircraft comprises an upper panel 42, a lower panel 44, a forward spar 46, and a rear spar 48, the forward and rear spars 46 and 48 being positioned in transverse planes offset along the longitudinal direction. The upper and lower panels 42 and 44, as well as the forward and rear spars 46 and 48, are connected in pairs at junctions oriented along a junction direction to form a box-section structure. Each has an inner face Fint facing the interior of the central wing box 40 and an outer face Fext opposite the inner face Fint. The inner and outer faces Fint and Fext of each panel or spar are substantially parallel to each other.

[0035] According to one configuration, the central wing box 40 includes stiffeners 50 positioned at the level of the inner face Fint of the upper and lower panels 42, 44 as well as the front and rear spars 46, 48, the stiffeners 50 being oriented in directions parallel to the direction of joining.

[0036] The central wing box 40 comprises at least one beam 52 positioned against the outer face Fext of at least one wall 54 among the upper and lower panels 42, 44 as well as the front and rear spars 46, 48, the beam 52 being connected to the wall 54 by connecting elements 56. According to one arrangement, the beam 52 is oriented in a direction parallel to the longitudinal direction.

[0037] In one configuration, the beam 52 comprises at least one first web 58 and at least one flange 60 connected to the first web 58 and attached to the outer face Fext of the wall 54. The first web 58 has first and second faces 58.1, 58.2 that are symmetrical with respect to a first median plane PMI parallel to the longitudinal direction. In one arrangement, the flange 60 is perpendicular to the first web 58 and extends on either side of it. In this arrangement, the beam 52 has an I-shaped or T-shaped cross-section. Of course, the invention is not limited to this cross-section for the beam 52.

[0038] According to one embodiment, each connecting element 56 has a rod 56.1 and, for each connecting element 56, the wall 54 and the flange 60 of the beam 52 each include an opening 54.1, 60.1 passing through the wall 54 and the flange 60 to allow the passage of the rod 56.1.

[0039] For each connecting element 56, the central wing box 40 includes at least one seal, such as a cord and / or a sealant coating, to obtain at the right of each connecting element 56 a watertight barrier between the inside and outside of the central wing box 40.

[0040] The upper and lower panels 42, 44, the front and rear stringers 46, 48, the stiffeners 50, the beams 52 and the connecting elements 56 are not further described as they may be identical to those of the prior art.

[0041] The central wing box 40 includes at least one attachment 62 projecting by relation to the inner face Fint of the wall 54 as well as at least one element 64, such as a connecting rod for example, positioned in the central wing box 40 and connected to the attachment 62.

[0042] According to one feature of the invention, the fastener 62 is integral with the beam 52 and the wall 54 includes, for each fastener 62, a through hole 66 to allow the fastener 62 to pass through the wall 54.

[0043] According to the invention, the beam 52 and the fastener 62 form a single and same piece made in one piece.

[0044] According to one embodiment, the fastener 62 comprises at least a second web 68 connected to the flange 60 of the beam 52, the first and second webs 58, 68 being positioned on either side of the flange 60. This second web 68 has first and second faces 68.1, 68.2 that are symmetrical with respect to a second median plane PM2. According to one arrangement, the second web 68 is aligned with the first web 58 of the beam 52. Thus, the first and second median planes PM1, PM2 are coplanar.

[0045] According to one arrangement, the sole 60 has substantially coplanar contact surfaces 70.1, 70.2, positioned on either side of the second web 68 and configured to be pressed against the external face Fext of the wall 54.

[0046] According to one configuration, the contact surfaces 70.1, 70.2 are substantially perpendicular to the second median plane PM2. However, the invention is not limited to this configuration.

[0047] The through hole 66 has a rectangular cross-section. Thus, the through hole 66 is delimited by first and second long edges 72.1, 72.2 that are substantially parallel to each other, as well as by first and second short edges 74.1, 74.2 that are substantially parallel to each other and connect the first and second long edges 72.1, 72.2. These edges 72.1, 72.2, 74.1, 74.2 are substantially perpendicular to the internal and external faces Fint, Fext. Unlike the prior art, no plate is pressed against the internal face Fint of the wall 54, which can remain in its raw state and does not need to be machined. According to the invention, only one plate, in this case the flange 60 of the beam 52, requires adjustment and shimming operations, unlike the prior art which requires adjustment and shimming operations for the flanges of the beam and the attachment.

[0048] The through hole 66 has a length corresponding to a distance separating the first and second short edges 74.1, 74.2 and a width corresponding to a distance separating the first and second long edges 72.1, 72.2.

[0049] The second web 68 has a thickness corresponding to a distance separating its first and second faces 68.1, 68.2, substantially equal to or very slightly less than the width of the through hole 66. The length of the through hole 66 is di mentioned so as to allow the passage of the second soul 68 while limiting the spacing between the second soul 68 and the first and second short sides 74.1, 74.2. Thus, the through hole 66 and the attachment 62 are configured so as to delimit a small spacing between the wall 54 and the attachment 62.

[0050] For each attachment 62, the central wing box 40 includes at least one seal 76, such as a bead of sealant and / or a sealant coating, to fill the gap between the wall 54 and the attachment 62, and more particularly its second web 68, to obtain, around the second web 68 of the attachment 62, a watertight barrier between the inside and outside of the central wing box 40.

[0051] The shapes of the second web 68 can be adapted to facilitate the placement of the seal 76 in the spacing between the second web 68 and the wall 54.

[0052] Alternatively, the seal 76 is positioned between the flange 60 of the beam 52 and the wall 54. Regardless of the variant, the central wing box 40 includes at least one seal 76 interposed between, on the one hand, the wall 54 and, on the other hand, the flange 60 and / or the second web 68 of the beam 52, configured to ensure fluid tightness between interior and exterior zones separated by the wall 54.

[0053] Several fasteners 62 can be connected to the same beam 52. According to one configuration, the central wing box 40 comprises several beams 52 oriented along the longitudinal direction and positioned against the external faces Fext of the upper and lower panels 42, 44. In addition, the central wing box 40 comprises at least one connecting rod 64 having a first end 64.1 connected to a first fastener 62 integral with a first beam 52 fixed against the external face Fext of the upper panel 42 and a second end 64.2 connected to a second fastener 62' integral with a second beam 52' fixed against the external face Fext of the lower panel 44.

[0054] According to one embodiment, each beam 52, 52' and the fasteners 62, 62' connected to said beam 52, 52' are made in one piece by any suitable manufacturing process.

[0055] For each fastener 62, 62', a through hole 66 is made in the wall 54 against which is fixed the beam 52, 52' to which is connected the fastener 62, 62'.

[0056] A method for assembling a beam 52, 52' includes a step of adjusting the position of the beam 52, 52' relative to the wall 54 by inserting the second web 68 of each fastener 62, 62' of the beam 52, 52' into a hole through 66, a step of drilling the holes 54.1, 60.1 through the wall 54 and the flange 60, a step of setting up the connecting elements 56 and then a step of installing a seal 76 to fill the gap between the second web 68 of each fastener 62, 62' and the wall 54.

[0057] The invention makes it possible to reduce the number of parts to be assembled, which makes it possible to simplify the assembly process and potentially automate it.

[0058] Of course, the invention is not limited to the wing center box. It can be applied to any assembly comprising a wall 54 having internal and external faces Fint, Fext, a beam 52 positioned against the external face Fext of the wall 54, and a fastener 62 projecting from the internal face Fint of the wall 54 and connected to the beam 52. In one application, the wall 54 separates, in a fluid-tight manner, external and internal zones. By way of example, a pressurization panel for a landing gear bay of an aircraft comprises a wall, at least one first beam attached to a first face of the wall (the one facing outwards from the landing gear bay) to reinforce it, and at least one fastener projecting from a second face of the wall (the one facing inwards from the landing gear bay) to which a second beam is connected.

Claims

Demands

1. Central wing box comprising: a. upper and lower panels (42, 44) and front and rear stringers (46, 48) connected in pairs to form a box-section structure and each having an inner face (Fint) and an outer face (Fext) opposite the inner face (Fint), a. at least one first beam (52) positioned against the external face (Fext) of the upper panel (42) and connected to the upper panel (42) by connecting elements (56), b. at least one second beam (52') positioned against the outer face (Fext) of the lower panel (44) and connected to the lower panel (44) by connecting elements, c. at least one first fastener (62) projecting from the inner face (Fint) of the upper panel (42) and at least one second fastener (62') projecting from the inner face (Fint) of the lower panel (44), d. at least one connecting rod (64) having a first end (64.1) connected to the first attachment (62) and a second end (64.2) connected to the second attachment (62'), e. characterized in that the first fastener (62) is integral with the first beam (52) and forms with the first beam (52) a single piece made in one piece, the upper panel (42) comprising, for each first fastener (62), a through hole (66) to allow the first fastener (62) to pass through the upper panel (42) and in that the second fastener (62') is integral with the second beam (52') and forms with the second beam (52') a single piece made in one piece, the lower panel (44) comprising, for each second fastener (62'), a through hole (66) to allow the second fastener (62') to pass through the lower panel (44).

2. Central wing box according to the preceding claim, characterized in that the first or second beam (52, 52') comprises at least a first web (58) and at least one flange (60) connected to the first web (58) and pressed against the outer face (Fext) of the upper or lower panel (42, 44) and in that the first or second attachment (62, 62') comprises a second web (68) connected to the flange (60) of the first or second beam (52, 52'), the first and second webs (58, 68) being positioned on either side of the flange (60).

3. Central wing box according to the preceding claim, characterized in that the first web (58) of the first or second beam (52) has a first median plane (PMI) and in that the second web (68) of the first or second attachment (62, 62') includes a second median plane (PM2), the first and second median planes (PMI, PM2) being coplanar.

4. Central wing box according to any one of the preceding claims, characterized in that the assembly comprises at least one seal (76) interposed between, on the one hand, the upper or lower panel (42, 44) and, on the other hand, the flange (60) and / or the second web (68) of the first or second beam (52, 52') and configured to ensure fluid tightness.

5. Central wing box according to any one of the preceding claims, characterized in that the through hole (66) and the first or second attachment (62, 62') are configured so as to delimit a small gap between the upper or lower panel (42, 44) and the first or second attachment (62, 62').

6. Central wing box according to claims 4 and 5, characterized in that the seal (76) is configured to fill the gap between the upper or lower panel (42, 44) and the first or second attachment (62, 62').

7. Aircraft comprising a central wing box according to any one of the preceding claims.

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