An assembly comprising at least one connecting element and at least two contact surfaces with asperities; an aircraft comprising at least one such assembly

Abstract

Assembly comprising at least one connecting element and at least two contact surfaces provided with asperities, aircraft comprising at least one such assembly. The invention relates to an assembly comprising at least first and second parts (22, 24), at least one connecting element (26) comprising a rod (28) configured to ensure the transfer of tensile / compressive forces between the first and second parts (22, 24), and at least one pair of first and second contact surfaces (32, 34) respectively provided with first and second asperities and respectively integral with the first and second parts (22, 24), the first and second asperities having complementary shapes configured to interlock with each other and ensure the transmission of shear forces between the first and second parts (22, 24). The invention also relates to an aircraft comprising at least one such assembly. Figure 2

Description

Title of the invention: Assembly comprising at least one connecting element and at least two contact surfaces provided with asperities, aircraft comprising at least one such assembly

[0001] The present application relates to an assembly comprising at least one connecting element and at least two contact surfaces provided with asperities as well as to an aircraft comprising at least one such assembly.

[0002] According to an embodiment visible in [Fig.l], an assembly comprises at least first and second parts 10, 12 each comprising internal and external faces 10.1, 12.1, 10.2, 12.2 as well as a through-orifice 10.3, 12.3 connecting the internal and external faces 10.1, 12.1, 10.2, 12.2. When the two parts 10 and 12 are assembled, the smooth internal faces 10.1, 12.1 are pressed against each other and the through-orifices 10.3, 12.3 are coaxial and have substantially the same diameter. The assembly comprises at least one connecting element 14 which has a rod 14.1 housed in the through holes 10.3, 12.3 as well as two stops 14.2, 14.3 connected by the rod 14.1 and pressed against the external faces 10.2, 12.2 of the first and second parts 10, 12.

[0003] The connecting element 14 is configured to ensure the transmission of the tensile / compressive and shear forces between the first and second parts 10, 12. To ensure the transmission of the shear forces, the through-orifices 10.3, 12.3 of the first and second parts 10, 12 must be coaxial and have internal diameters that are substantially equal to each other and adjusted to the external diameter of the rod 14.1 of the connecting element 14. By adjusted, it is meant that there remains a very small, or even zero, clearance between the rod 14.1 and the first and second parts 10, 12.

[0004] When the first and second parts 10, 12 correspond to first and second structures of an aircraft each composed of several elements assembled together, it is very difficult to obtain coaxial through-holes 10.3, 12.3 before the first and second parts 10, 12 are pre-positioned to be assembled. Consequently, to assemble the first and second parts 10, 12, the latter are pre-positioned, drilled simultaneously to obtain perfectly coaxial through-holes 10.3, 12.3 of the same diameter and then assembled by putting in place the connecting element 14.

[0005] This method of assembly is not fully satisfactory because it takes a relatively long time to implement, which tends to increase the assembly time of an aircraft.

[0006] According to another disadvantage, when the first part is a part which must be disassembled and reassembled several times during the operation of the aircraft, it is necessary that the through-holes 10.3, 12.3 are repositioned coaxially during each reassembly. Consequently, at each reassembly, the through-holes 10.3, 12.3 of the first and second parts 10, 12 must be remachined so that they are perfectly coaxial. This machining leads to an increase in the diameter of the through-holes 10.3, 12.3 so that the connecting element 14 replaced must have a rod of larger section with a diameter adjusted to that of the enlarged through-holes 10.3, 12.3, which tends to increase the on-board mass. In addition, in certain cases, this machining operation is incompatible with certain equipment positioned near the through-holes 10.3, 12.3.

[0007] The present invention aims to remedy all or part of the drawbacks of the prior art.

[0008] To this end, the invention relates to an assembly comprising at least first and second parts as well as at least one connecting element comprising a rod configured to ensure a take-up of the tensile / compressive forces between the first and second parts, the first part comprising a first internal face oriented towards the second part and a first through-orifice configured to house the rod, the second part comprising a second internal face oriented towards the first part and a second through-orifice configured to house the rod.

[0009] According to the invention, the assembly comprises at least one pair of first and second contact surfaces pressed against each other, the first contact surface being integral with the first part and provided with first asperities, the second contact surface being integral with the second part and provided with second asperities, the first and second asperities having complementary shapes configured to fit into each other and ensure transmission of shear forces between the first and second parts.

[0010] According to the invention, the transmission of the shear forces is ensured by elements distinct from the rod of the connecting element. Consequently, the through holes of the first and second parts are not necessarily adjusted to the diameter of the rod of the connecting element and can be produced independently of each other, prior to assembly.

[0011] According to another characteristic, the first and second asperities are respectively first and second grooves.

[0012] According to another characteristic, the assembly comprises at least one plate inserted between the first and second internal faces of the first and second parts, the plate being integral with a first element among the first and second parts and comprising the first contact surface provided with the first grooves oriented towards a second element, different from the first element, among the first and second parts, the second element comprising the second contact surface provided with the second grooves and pressed against the first contact surface, the assembly comprising at least one fixing element connecting the plate and the first element, configured to ensure at least partial transmission of the shear forces between the first and second parts.

[0013] According to another characteristic, the assembly comprises first and second plates interposed between the first and second internal faces of the first and second parts, the first and second plates being respectively integral with the first and second parts and respectively comprising the first and second contact surfaces provided with the first and second grooves.

[0014] According to another characteristic, each plate comprises at least one through-hole for housing the rod of the connecting element.

[0015] According to another characteristic, the first internal face of the first part is flat and smooth. In addition, the first plate is connected to the first part by at least one first fixing element configured to ensure at least partial absorption of the shear forces between the first and second parts, said first plate comprising a first flat and smooth face pressed against the first internal face of the first part.

[0016] According to another characteristic, the second internal face of the second part is flat and smooth. In addition, the second plate is connected to the second part by at least one second fixing element configured to ensure at least partial absorption of the shear forces between the first and second parts, said second plate comprising a second flat and smooth face pressed against the second internal face of the second part.

[0017] According to another characteristic, each plate comprises an extension crossed by at least one fixing element, having a thickness less than that of the rest of the plate.

[0018] According to another characteristic, at least one part among the first and second parts comprises at least one recessed housing relative to the first or second internal face of the first or second part, configured to house at least one first or second plate.

[0019] According to another characteristic, the first and second grooves are rectilinear and parallel to each other and oriented in a direction perpendicular to a direction of absorption of the shear forces.

[0020] According to another characteristic, the first and second grooves are concentric circles around the rod of the connecting element.

[0021] According to another characteristic, the first and second grooves have a height of between 1 and 5 mm.

[0022] The invention also relates to an aircraft comprising at least one assembly according to one of the preceding characteristics.

[0023] According to one application, the aircraft comprises a frame delimiting an opening, a removable panel configured to close the opening as well as at least one assembly connecting the frame and the panel which correspond respectively to the first and second parts of the assembly.

[0024] According to another application, the aircraft comprises at least two fuselage sections respectively comprising first and second transverse reinforcements pressed against each other as well as at least one assembly connecting the first and second transverse reinforcements which correspond respectively to the first and second parts of the assembly.

[0025] According to another application, the aircraft comprises a central wing box comprising a first structure, a second structure as well as at least one assembly connecting the first and second structures which correspond respectively to the first and second parts of the assembly.

[0026] The invention also relates to a mounting method comprising a step of positioning the first and second plates between the first and second parts, at least one of them not being secured to the first or second part, a step of positioning the first and second parts relative to each other in a desired position, a step of holding the first and second parts in this desired position by placing at least one connecting element, the first and second grooves interlocking with each other during this placing, a step of fixing the first and second plates, not yet secured, respectively to the first and second parts,each of the first and second plates being secured to the first or second part by at least one fixing element configured to ensure at least partial transmission of the shear forces between the first and second parts.

[0027] According to another characteristic, the first and second grooves are configured as a function of the deformations of the first and second parts during disassembly in order to compensate for said deformations during reassembly.

[0028] According to another characteristic, the first and second grooves are oriented, during assembly, perpendicular to at least one direction of movement of the first and second parts relative to each other during disassembly.

[0029] Other characteristics and advantages will emerge from the description of the invention which follows, a description given by way of example only, with reference to the appended drawings, among which:

[0030] [Fig-1] is a cross-section of an assembly illustrating an embodiment of the prior art,

[0031] [Fig.2] is a cross-section of an assembly illustrating one embodiment of the invention,

[0032] [Fig.3] is a front view of a portion of a contact surface illustrating a mode of carrying out the invention,

[0033] [Fig.4] is a front view of a portion of a contact surface illustrating another embodiment of the invention,

[0034] [Fig.5] is a perspective view of an aircraft,

[0035] [Fig.6] is a perspective view of a portion of an aircraft fuselage comprising a removable structure connected to a fixed structure by at least one assembly illustrating an embodiment of the invention,

[0036] [Fig.7] is a cross-section of part of the removable and fixed structures visible in [Fig.6], connected by at least one assembly,

[0037] [Fig.8] is a cross-section of the assembly visible in [Fig.7] illustrating a first embodiment of the invention,

[0038] [Fig.9] is a cross-section of the assembly visible in [Fig.7] illustrating a second embodiment of the invention,

[0039] [Fig. 10] is a cross-section of an aircraft fuselage illustrating one embodiment of the invention,

[0040] [Fig. 11] is a front view of an assembly connecting two fuselage sections illustrating an embodiment of the invention,

[0041] [Fig. 12] is a section along line AA of [Fig. 11] of an assembly illustrating an embodiment of the invention,

[0042] [Fig. 13] is a longitudinal section of a central wing box of an aircraft illustrating an embodiment of the invention,

[0043] [Fig. 14] is a cross-section of a portion of two structures of the central wing box connected by at least one assembly illustrating an embodiment of the invention,

[0044] [Fig. 15] is a front view of the assembly visible in [Fig. 14],

[0045] [Fig. 16] is a cross-section of first and second inserts illustrating an embodiment of the invention, before tightening on part (A) and after tightening on part (B).

[0046] According to an embodiment visible in [Fig. 2], an assembly 20 comprises at least first and second parts 22, 24, the first part 22 comprising a first internal face 22.1 oriented towards the second part 24, a first external face 22.2 opposite the first internal face 22.1 as well as a first through-orifice 22.3 opening at the level of the first internal and external faces 22.1, 22.2, the second part 24 comprising a second internal face 24.1 oriented towards the first part 22, a second external face 24.2 opposite the second internal face 24.1 as well as a second through-orifice 24.3 opening at the level of the second internal and external faces 24.1, 24.2.

[0047] Around the first through-orifice 22.3, the first internal and external faces 22.1, 22.2 are substantially flat and parallel to each other. The first through-orifice 22.3 has a first internal diameter and a first axis A22 substantially perpendicular to the first internal and external faces 22.1, 22.2.

[0048] Around the second through-hole 24.3, the second internal and external faces 24.1, 24.2 are substantially flat and parallel to each other. The second through-hole 24.3 has a second internal diameter and a second axis A24 substantially perpendicular to the second internal and external faces 24.1, 24.2.

[0049] The assembly 20 comprises at least one connecting element 26 connecting the first and second parts 22, 24, comprising a rod 28 positioned in the through-holes 22.3, 24.3 as well as first and second stops 30.1, 30.2 connected by the rod 28 and configured to be pressed respectively against the first and second external faces 22.2, 24.2. According to one embodiment, the connecting element 26 is a bolt or a rivet.

[0050] The rod 28 is cylindrical and has an axis A28 substantially perpendicular to the first and second external faces 22.2, 24.2 of the first and second parts 22, 24.

[0051] Each connecting element 26 is configured to ensure the transmission of tensile / compressive forces between the first and second parts 22, 24.

[0052] The rod 28 has an outside diameter smaller than the inside diameter of the first and second through-holes 22.3, 24.3. Unlike the prior art, the assembly 20 comprises a clearance greater than 1 mm, generally greater than 2 mm, between the rod 28 and at least one of the first and second parts 22, 24. Consequently, the rod 28 is not configured to ensure the transmission of shear forces and the first and second through-holes 22.3, 24.3 are not necessarily coaxial.

[0053] According to the invention, the first and second through-holes 22.3, 24.3 can be produced independently of each other, prior to assembly. Thus, the first and second parts 22, 24 are not drilled simultaneously during assembly and the assembly method does not include a drilling step. This solution simplifies assembly insofar as the first and second through-holes 22.3, 24.3 can be produced before assembly of the first and second parts 22, 24.

[0054] According to one configuration, the assembly 20 comprises a first clearance greater than 2 mm between the rod 28 and the first part 22 and / or a second clearance greater than 2 mm between the rod 28 and the second part 24.

[0055] Of course, the invention is not limited to this embodiment for the element of connection 26. According to another embodiment, the rod 28 has a first end connected to the first part by screwing the rod directly into a tapped hole provided in the first part or indirectly into a “barrel nut” type nut positioned in a housing provided in the first part 22. Whatever the embodiment, each connecting element 26 comprises a rod 28 configured to ensure the absorption of the tensile / compressive forces between the first and second parts 22, 24.

[0056] The assembly also comprises at least one pair of first and second contact surfaces 32, 34, the first contact surface 32 being integral with the first part 22 and provided with first grooves S32, the second contact surface 34 being integral with the second part 24 and provided with second grooves S34, the first and second contact surfaces 32, 34 being pressed against each other, at a contact plane P, so that the first and second grooves S32, S34 are nested within each other so that the first and second parts 22, 24 are immobilized relative to each other in at least one direction perpendicular to the axis A28 of the rod 28.

[0057] By striations, we mean a succession of alternating furrows (hollow) and ribs (projecting).

[0058] The first and second grooves S32, S34 are configured to ensure transmission of shear forces between the first and second parts 22, 24. The first and second grooves S32, S34 have complementary shapes so that there is no space between the first and second contact surfaces 32, 34 when they are pressed against each other. The number and shapes of the first and second grooves S32, S34 are adjusted according to the shear forces to be transmitted. Of course, the invention is not limited to the grooves as shapes to ensure transmission of shear forces between the first and second parts 22, 24. Thus, the grooves can be replaced by other asperities.More generally, the first and second contact surfaces 32, 34 respectively comprise first and second asperities having complementary shapes configured to fit into each other when the first and second contact surfaces 32, 34 are pressed against each other and to ensure transmission of shear forces between the first and second parts 22, 24.

[0059] According to the invention, the absorption of the traction / compression forces is dissociated from the absorption of the shear forces, each of them being ensured by separate elements, namely the connecting element 26 for the traction / compression forces and the pair of first and second contact surfaces 32, 34 provided with asperities for the shear forces. Consequently, it is possible to optimize the dimension sioning of the connecting element 26 for the absorption of tensile / compressive forces (without taking into account the shear forces) as well as the dimensioning of the first and second grooves S32, S34 for the absorption of shear forces (without taking into account the tensile / compressive forces).

[0060] According to a first configuration visible in [Fig. 3], the first and second grooves S32, S34 are rectilinear and parallel to each other and oriented in a direction perpendicular to a direction of absorption of the shear forces. This first configuration allows absorption of the shear forces in a preferred direction perpendicular to the direction of the grooves S32, S34.

[0061] According to a second configuration visible in [Fig.4], the first and second grooves S32, S34 are concentric circles around the rod 28 of the connecting element 26. This second configuration allows omnidirectional shear stress absorption.

[0062] According to one arrangement, the first and second grooves S32, S34 have a height of between 1 and 5 mm. Each groove S32, S34 comprises two inclined sides forming an angle of between 10 and 45° relative to a straight line perpendicular to the internal face 22.1, 24.1 of the first or second part 22, 24. The grooves S32, S34 may have angular, rounded or truncated vertices.

[0063] According to one embodiment, for at least one of the first and second parts 22, 24, at least one striated contact surface 32, 34 corresponds to the internal face 22.1, 24.1 of the first or second part 22, 24.

[0064] According to another embodiment, for the first and second parts 22, 24, the first and second contact surfaces 32, 34 correspond respectively to the first and second internal faces 22.1, 24.1 of the first and second parts 22, 24.

[0065] According to another embodiment, the assembly 20 comprises at least one plate 36, interposed between the first and second internal faces 22.1, 24.1 of the first and second parts 22, 24, the plate 36 being integral with a first element among the first and second parts and comprising a first contact surface 32 provided with first grooves S32 oriented towards a second element, different from the first element, among the first and second parts 22, 24, the second element comprising a second contact surface 34 provided with second grooves S34 and pressed against the first contact surface 32. According to one arrangement, the plate 36 comprises at least one through-orifice 36.1 for housing the rod 28 of a connecting element 26. This arrangement allows the plate 36 to be held in place, crossed by the connecting element 26, before it is tightened.

[0066] According to one embodiment, the assembly 20 comprises at least one fixing element 40 connecting the plate 36 and the first element, this (or these) fixing element(s) 40 being configured to ensure at least partial absorption of the forces of shear between the plate 36 and the first element. This (or these) fixing element(s) 40 is (are) sized according to the shear forces to be transmitted between the first and second parts 22, 24.

[0067] Each fastening element 40 comprises a rod having a given section depending on the shear forces to be transmitted. For example, each fastening element 40 is a pin, a screw or a shear rivet. For each fastening element 40, the plate 36 and the first element each comprise a housing, such as a through-hole for example, configured to house the rod of the fastening element 40, said housing having a section adjusted to that of the rod of the fastening element 40. For information, a clearance of the order of 1 / 100th to 2 / 100th is provided between the wall of each housing and the rod of the fastening element 40 to allow the insertion of the fastening element 40 into the housing. Alternatively, the fastening element 40 could be force-fitted into its housing.

[0068] According to an embodiment visible in [Fig.2], the assembly 20 comprises first and second plates 36, 38, interposed between the first and second internal faces 22.1, 24.1 of the first and second parts 22, 24, the first and second plates 36, 38 being respectively integral with the first and second parts 22, 24 and respectively comprising the first and second contact surfaces 32, 34 provided with the first and second grooves S32, S34. According to this embodiment, the first and second contact surfaces 32, 34 are distinct from the first and second parts 22, 24. According to one arrangement, the first and second plates 36, 38 each comprise at least one through-orifice 36.1, 38.1 for housing the rod 28 of a connecting element 26.

[0069] According to one configuration, the first internal face 22.1 of the first part 22 is flat and smooth. In addition, the first plate 36 is connected to the first part 22 by at least one first fixing element 40 and comprises a first flat and smooth face 36.2 pressed against the first internal face 22.1 of the first part 22 as well as a first contact surface 32 opposite the first flat and smooth face 36.2, provided with first grooves S32 and oriented towards the second plate 38. The second internal face 24.1 of the second part 24 is flat and smooth. In addition, the second plate 38 is connected to the second part 24 by at least one second fixing element 42 and comprises a second flat and smooth face 38.2 pressed against the second internal face 24.1 of the second part 24 as well as a second contact surface 34 opposite the second flat and smooth face 38.2, provided with second grooves S34 and oriented towards the first plate 36.The fixing elements 40, 42 are configured to ensure a recovery of the shear forces between the first plate 36 and the first part 22 as well as between the second plate 38 and the second part 24. They are sized according to the shear forces. shear to be transmitted between the first and second parts 22, 24.

[0070] By way of example, the first and second fastening elements 40, 42 are pins, rivets or shear bolts. Of course, the invention is not limited to this embodiment for securing a plate and a part. Alternatively, the first or second plate 36, 38 could be glued or welded to the first or second part 22, 24. A first or second plate 36, 38 may be connected to the first or second part 22, 24 by one or more fastening element(s) 40, 42. Whatever the embodiment, each plate 36, 38 is connected to the first or second part 22, 24 by at least one fastening element 40, 42 configured to ensure at least partial transmission of the shear forces between the first and second parts 22, 24.

[0071] According to one embodiment, each plate 36, 38 comprises a single through-orifice 36.1, 38.1. In this case, the plate 36, 38 is crossed by a single connecting element 26. According to another embodiment visible in [Fig. 10], each plate 36, 38 comprises several through-orifices 36.1, 38.1. In this case, the plate 36, 38 is crossed by several connecting elements 26.

[0072] According to an embodiment visible in [Fig.2], the first and second plates 36, 38 protrude relative to the first and second internal faces 22.1, 24.1 of the first and second parts 22, 24.

[0073] According to another embodiment visible in [Fig. 11], at least one part among the first and second parts 22, 24 comprises at least one housing 44 hollow relative to the first or second internal face 22.1, 24.1 of the first or second part 22, 24, configured to house at least one first or second plate 36, 38. The housing 44 has a contour 44.1 substantially equal to that of at least one of the first and second plates 36, 38. The housing 44 has a depth (dimension taken perpendicular to the first or second internal face 22.1, 24.1) configured to house at least one of the first and second plates 36, 38. According to one configuration, the first part 22 comprises a first housing 44 configured to house the first plate 36 and the second part 24 comprises a second housing configured to house the second plate 38. According to another configuration visible in [Fig.l 1], only the first part 22 comprises a housing configured to house the first and second plates 36, 38. .

[0074] According to one arrangement, at least one plate 36, 38 and its housing 44 are configured to ensure at least partial absorption of the shear forces between the plate 36, 38 and the first or second part 22, 24 in which the housing 44 is formed.

[0075] As illustrated in [Fig.12], each plate 36, 38 comprises an extension 46 (which does not cooperate with the other plate) crossed by at least one element of fixing 40, 42. According to an embodiment visible in [Fig. 12], the extension 46 has a thickness less than that of the rest of the plate 36, 38.

[0076] For a first assembly, the first plate 36 is connected to the first part 22 by means of a first fixing element 40, then the second plate 38, not connected to the second part 24, is positioned relative to the first plate 36 and held assembled with the latter by a temporary connection such as an adhesive for example. Next, the second part 24 is positioned relative to the second plate 38 and connected to the latter by means of a second fixing element 42. Finally, the connecting element 26 is put in place and tightened.

[0077] According to one operating mode, a mounting method comprises a step of positioning the first and second plates 36, 38 between the first and second parts 22, 24, at least one of them not being secured to the first or second part 22, 24, a step of positioning the first and second parts 22, 24 relative to each other in a desired position, a step of holding the first and second parts 22, 24 in this desired position by placing at least one connecting element 26, during this placing, the first and second grooves S32, S34 interlocking with each other, a step of fixing the first and second plates 36, 38, not yet secured, respectively to the first and second parts 22, 24, each of the first and second plates 36, 38 being secured to the first or second part 22, 24 by at least one connecting element 26. at least one fixing element 40,42 configured to ensure at least partial transmission of the shear forces between the first and second parts 22, 24.,

[0078] According to one application, an aircraft 50 comprises at least one assembly 20 as previously described.

[0079] In a known manner, the aircraft 50 comprises a fuselage 52, wings 54 positioned on either side of the fuselage 52 as well as a central wing box 56 (visible in [Fig. 13]) connecting the wings 54 and the fuselage 52. The latter comprises several sections 58 positioned end to end.

[0080] According to a first application visible in figures 6 to 9, the fuselage 52 comprises a frame 60 delimiting an opening 60.1, a removable panel 62 configured to close the opening 60.1 as well as at least one assembly 20 connecting the panel 62 and the frame 60. According to this application, the frame 60 corresponds to the first part 22 of the assembly 20 and the panel 62 corresponds to the second part 24 of the assembly 20.

[0081] According to one arrangement, the fuselage comprises several assemblies 20 distributed around the periphery of the panel 62.

[0082] Each assembly 20 comprises a connecting element 26 as well as first and second plates 36, 38 connected respectively to the frame 60 and to the panel 62. According to a first variant visible in [Fig.8], the first and second grooves S32, S34 are circular and concentric around the connecting element 26. According to a second variant visible in [Fig.9], the first and second grooves S32, S34 are rectilinear and parallel to each other.

[0083] The fuselage 52 comprises an outer wall 64 forming the skin of the aircraft 50. According to one arrangement, each assembly 20 has a contact plane P which forms an angle of the order of 45° with the outer wall 64. This inclination of the contact plane P facilitates the reassembly of the panel 62.

[0084] According to a second application visible in Figures 10 to 12, the fuselage 52 comprises at least two sections 58, 58' connected by at least one assembly 20. Each section 58, 58' of the fuselage 52 comprises several transverse reinforcements 66, 66' as well as an outer wall 68, 68' attached to the transverse reinforcements 66, 66'. The first and second sections 58, 58' respectively comprise first and second transverse reinforcements 66, 66' pressed against each other, at least one assembly 20 connecting the first and second transverse reinforcements 66, 66' which correspond respectively to the first and second parts 22, 24 of the assembly 20.

[0085] The assembly 20 connecting the first and second sections 58, 58' comprises several pairs of first and second plates 36, 38 distributed regularly around the first and second transverse reinforcements 66, 66', the first plates 36 being connected to the first transverse reinforcement 66, the second plates 38 being connected to the second transverse reinforcement 66'. Each first or second plate 36, 38 is in the form of a ring sector which has the same radius of curvature as the first or second transverse reinforcement 66, 66' to which it is connected. According to one arrangement, the assembly comprises eight pairs of first and second plates 36, 38.

[0086] Each of the first and second plates 36, 38 is connected to the first or second transverse reinforcement 66, 66' by several fixing elements 40, 42. Each of the first and second plates 36, 38 is crossed by several connecting elements 26.

[0087] According to a third application visible in figures 13 to 15, the central wing box 56 comprises a first structure 70, a second structure 72 as well as at least one assembly 20 connecting the first and second structures 70, 72, the first and second structures corresponding respectively to the first and second parts 22, 24 of the assembly 20.

[0088] The first structure 70 comprises at least one first panel 70.1 as well as at least one first bracket 70.2 connected to the first panel 70.1. According to one arrangement, the first structure 70 comprises at least one first panel 70.1 and, for each first panel 70.1, two first brackets 70.2, 70.3 arranged in on either side of the first panel 70.1. The first brackets 70.2, 70.3 have first coplanar SI joining surfaces.

[0089] The second structure 72 comprises at least one second panel 72.1 as well as at least one second bracket 72.2 connected to the second panel 72.1. According to one arrangement, the second structure 72 comprises at least one second panel 72.1 and, for each second panel 72.1, two second brackets 72.2, 72.3 arranged on either side of the second panel 72.1. The second brackets 72.2, 72.3 have second coplanar joining surfaces S2.

[0090] The assembly 20 comprises at least one pair of first and second plates 36, 38, the first plate 36 of each pair being connected to a first bracket 70.2, 70.3 and pressed against the first junction surface SI, the second plate 38 of each pair being connected to a second bracket 72.2, 72.3.

[0091] The assembly 20 may comprise one or more pairs of first or second plates 36, 38, each of the first and second plates 36, 38 being connected to a first or second bracket 70.2, 70.3, 72.2, 72.3 by one or more fixing element(s) 40, 42 and crossed by one or more connecting element(s) 26.

[0092] According to an arrangement visible in [Fig. 14], the second structure 72 comprises a partition 74, substantially perpendicular to the second panel 72.1, interposed between the second plates 38 and the second brackets 72.2, 72.3.

[0093] According to an embodiment illustrated by [Fig. 16], after disassembly, the first and second plates 36, 38 are used to reposition the first and second parts 22, 24 during reassembly.

[0094] As illustrated in [Fig. 16], the grooves S32, S34 of the same assembly may not all be identical. Thus, the same pair of contact surfaces 32, 34 comprises a first series of first and second grooves S32, S34 sized to ensure a take-up of the shear forces as well as a second series of first and second grooves S32', S34' configured to ensure a repositioning of the first and second parts 22, 24 relative to each other and a take-up of at least part of the shear forces. The first and second grooves S32', S34' of the second series have a height H' greater than the height H of the first and second grooves S32, S34 of the first series.

[0095] Alternatively, all the first or second ridges S32, S34 are identical and are configured to ensure repositioning of the first and second parts 22, 24 relative to each other and a recovery of the shear forces. Whatever the variant, the first and second ridges S32, S34, S32', S34' are configured (height, inclination, orientation) to reposition the first and second parts 22, 24 in the same position as during the first assembly during the various re- subsequent assemblies.

[0096] According to one operating mode, during disassembly and until reassembly, the first and second plates 36, 38 remain respectively secured to the first and second parts 22, 24. During reassembly, the first and second grooves S32', S34' are positioned so as to make the same grooves S32', S34' cooperate with each other as during the first assembly. As illustrated in part (A) of [Fig. 16], since the grooves S32', S34' are not completely nested within each other, the first and second parts 22, 24 can be offset relative to each other. When the connecting element 26 (or the connecting elements 26) is tightened, the grooves S32', S34' nest within each other. Due to the inclined sides of the grooves S32', S34', if necessary, the first and second parts 22, 24 move relative to each other so as to reach the same position as during the first assembly.

[0097] As illustrated in parts (A) and (B) of [Fig. 16], the first and second grooves S32', S34' are oriented according to the desired displacement DI between the first and second parts 22, 24 during repositioning. Thus, during the first assembly, the grooves S32, S34 are oriented according to the displacement DI to be carried out between the first and second parts 22, 24 to compensate for the deformations of at least one of them during disassembly. If the first and second parts 22, 24 tend to deform in a direction DI during disassembly and a displacement in the direction DI in the opposite direction between the first and second parts 22, 24 is necessary during reassembly, the grooves S32, S34 are oriented during the first assembly so that their crests are oriented perpendicular to the direction DI.

[0098] In the presence of first and second parts 22, 24 of large dimensions, the first and second striations S32, S34 of the assembly are not necessarily all oriented in the same way. If a first zone of one of the parts 22, 24 has a tendency to deform in a first direction, the first and second striations S32, S34 present in this first zone will be oriented perpendicular to this first direction. If a second zone of one of the parts 22, 24 has a tendency to deform in a second direction (intersecting the first direction), the first and second striations S32, S34 in this second zone will be oriented perpendicular to the second direction.

[0099] According to one operating mode, during a first assembly, the first and second grooves S32, S34 are configured not only as a function of the shear forces to be transmitted between the first and second parts 22, 24 but also as a function of the deformations of the first and second parts 22, 24 during disassembly in order to compensate for said deformations during reassembly. Thus, if the first and second parts 22, 24 move relative to each other according to at least a first direction during disassembly, the first and second grooves S32, S34 are oriented perpendicular to said at least one first direction during the first assembly.

[0100] If during disassembly the first and second parts 22, 24 deform relative to each other differently from one zone to another, the first and second grooves S32, S34 are configured, during a first assembly, zone by zone according to the deformations of the first and second parts 22, 24 during disassembly.

Claims

Claims

1. Assembly comprising at least first and second parts (22, 24) as well as at least one connecting element (26) comprising a rod (28) configured to ensure a take-up of the tensile / compressive forces between the first and second parts (22, 24), the first part (22) comprising a first internal face (22.1) oriented towards the second part (24) and a first through-orifice (22.3) configured to house the rod (28), the second part (24) comprising a second internal face (24.1) oriented towards the first part (22) and a second through-orifice (24.3) configured to house the rod (28); characterized in that the assembly (20) comprises at least one pair of first and second contact surfaces (32, 34) pressed against each other, the first contact surface (32) being integral with the first part (22) and provided with first asperities, the second contact surface (34) being integral with the second part (24) and provided with second asperities, the first and second asperities having complementary shapes configured to fit into each other and ensure transmission of shear forces between the first and second parts (22, 24).

2. Assembly according to the preceding claim, characterized in that the first and second asperities are respectively first and second grooves (S32, S34).

3. Assembly according to the preceding claim, characterized in that the assembly (20) comprises at least one plate (36) interposed between the first and second internal faces (22.1, 24.1) of the first and second parts (22, 24), the plate (36) being integral with a first element among the first and second parts (22, 24) and comprising the first contact surface (32) provided with the first grooves (S32) oriented towards a second element, different from the first element, among the first and second parts (22, 24), the second element comprising the second contact surface (34) provided with the second grooves (S34) and pressed against the first contact surface (32), the assembly comprising at least one fixing element (40) connecting the plate (36) and the first element, configured to ensure at least partial transmission of the shear forces between the first and second parts (22, 24).

4. Assembly according to the preceding claim, characterized in that the assembly (20) comprises first and second plates (36, 38) interposed between the first and second internal faces (22.1, 24.1) of the first and second parts (22, 24), the first and second plates (36, 38) being respectively integral with the first and second parts (22, 24) and respectively comprising the first and second contact surfaces (32, 34) provided with the first and second grooves (S32, S34).

5. Assembly according to the preceding claim, characterized in that each plate (36, 38) comprises at least one through-orifice (36.1) for housing the rod (28) of the connecting element (26).

6. Assembly according to the preceding claim, characterized in that the first internal face (22.1) of the first part (22) is flat and smooth and in that the first plate (36) is connected to the first part (22) by at least one first fixing element (40) configured to ensure at least partial absorption of the shear forces between the first and second parts (22, 24), said first plate (36) comprising a first flat and smooth face (36.2) pressed against the first internal face (22.1) of the first part (22).

7. Assembly according to one of claims 4 to 5, characterized in that the second internal face (24.1) of the second part (24) is flat and smooth and in that the second plate (38) is connected to the second part (24) by at least one second fixing element (42) configured to ensure at least partial absorption of the shear forces between the first and second parts (22, 24), said second plate (38) comprising a second flat and smooth face (38.2) pressed against the second internal face (24.1) of the second part (24).

8. Assembly according to one of claims 4 to 7, characterized in that each plate (36, 38) comprises an extension (46) crossed by at least one fixing element (40, 42), having a thickness less than that of the rest of the plate (36, 38).

9. Assembly according to one of claims 4 to 8, characterized in that at least one part among the first and second parts (22, 24) comprises at least one housing (44) hollow relative to the first or second internal face (22.1, 24.1) of the first or second part (22, 24), configured to house at least one first or second plate (36, 38).

10. Assembly according to one of claims 4 to 9, characterized in that the first and second striations (S32, S34) are rectilinear and parallel to each other and oriented in a direction perpendicular to a direction of absorption of the shear forces.

11. Assembly according to one of claims 4 to 9, characterized in that the first and second grooves (S32, S34) are concentric circles around the rod (28) of the connecting element (26).

12. Assembly according to one of claims 2 to 11, characterized in that the first and second grooves (S32, S34) have a height of between 1 and 5 mm.

13. Aircraft comprising at least one assembly according to one of the preceding claims.

14. Aircraft according to the preceding claim, characterized in that the aircraft comprises a frame (60) delimiting an opening (60.1), a removable panel (62) configured to close the opening (60.1) as well as at least one assembly (20) according to one of claims 1 to 12 connecting the frame (60) and the panel (62) which correspond respectively to the first and second parts (22, 24) of the assembly (20).

15. Aircraft according to claim 13, characterized in that the aircraft comprises at least two fuselage sections (58, 58') respectively comprising first and second transverse reinforcements (66, 66') pressed against each other as well as at least one assembly (20) according to one of claims 1 to 12 connecting the first and second transverse reinforcements (66, 66') which correspond respectively to the first and second parts (22, 24) of the assembly.

16. Aircraft according to claim 13, characterized in that the aircraft comprises a central wing box (56) comprising a first structure (70), a second structure (72) as well as at least one assembly (20) according to one of claims 1 to 12 connecting the first and second structures (70, 72) which correspond respectively to the first and second parts (22, 24) of the assembly (20).

17. Method for mounting an assembly according to one of claims 4 to 10, characterized in that a mounting method comprises a step of positioning the first and second plates (36, 38) between the first and second parts (22, 24), at least one of them not being secured to the first or second part (22, 24), a step of positioning the first and second parts (22, 24) relative to each other in a desired position, a step of holding the first and second parts (22, 24) in this desired position by placing at least one connecting element (26), the first and second grooves (S32, S34) interlocking with each other during this placing, a step of fixing the first and second plates (36, 38), not yet secured, respectively to the first and second parts (22, 24), each of the first and second plates (36, 38) being secured to the first or second part (22, 24) by at least one fixing element (40, 42) configured to ensure at least partial transmission of the shear forces between the first and second parts (22, 24).

18. Mounting method according to the preceding claim, characterized in that the first and second grooves (S32, S34) are configured according to the deformations of the first and second parts (22, 24) during disassembly in order to compensate for said deformations during reassembly.

19. Mounting method according to the preceding claim, characterized in that the first and second grooves (S32, S34) are oriented, during mounting, perpendicular to at least one direction of movement of the first and second parts (22, 24) relative to each other during disassembly.

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