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 and to an aircraft comprising at least one such assembly.

[0002] According to an embodiment visible in [Fig. 1], an assembly comprises at least first and second parts 10, 12, each having internal and external faces 10.1, 12.1, 10.2, 12.2 and a through hole 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 holes 10.3, 12.3 are coaxial and have substantially the same diameter. The assembly includes at least one connecting element 14 which has a rod 14.1 housed in the through holes 10.3, 12.3 and 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 tensile / compressive and shear forces between the first and second parts 10, 12. To ensure the transmission of shear forces, the through holes 10.3, 12.3 of the first and second parts 10, 12 must be coaxial and have substantially equal internal diameters and fit to the external diameter of the rod 14.1 of the connecting element 14. By fit, it is understood 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 the 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 for assembly. Therefore, to assemble the first and second parts 10, 12, they are pre-positioned, drilled simultaneously to obtain perfectly coaxial through holes 10.3, 12.3 of the same diameter, and then assembled by installing the connecting element 14.

[0005] This assembly method is not entirely satisfactory because it is relatively time-consuming to implement, which tends to increase the assembly time of an aircraft.

[0006] According to another drawback, when the first part is a part that must be disassembled and reassembled several times during the operation of the aircraft, it is necessary that the through holes 10.3, 12.3 be 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 results in an increase in the diameter of the through holes 10.3, 12.3, so that the reinstalled connecting element 14 must have a larger cross-section rod with a diameter adjusted to that of the enlarged through holes 10.3, 12.3, which tends to increase the onboard mass. Furthermore, in some 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 and at least one connecting element comprising a rod configured to ensure the transfer of 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 interlock with each other and ensure a transmission of shear forces between the first and second parts.

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

[0011] According to another feature, the first and second asperities are respectively first and second striations.

[0012] According to another feature, the assembly comprises at least one plate interposed between the first and second inner faces of the first and second parts, the plate being integral with a first element among the first and second parts and having 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 having the second surface of contact provided with the second grooves and pressed against the first contact surface, the assembly comprising at least one fixing element linking the plate and the first element, configured to ensure at least partial transmission of shear forces between the first and second parts.

[0013] According to another feature, 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 solid to 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 feature, each plate has at least one through hole to accommodate the rod of the connecting element.

[0015] According to another feature, the first inner 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 fastening element configured to ensure at least partial transfer of the shear forces between the first and second parts, said first plate comprising a first flat and smooth face pressed against the first inner face of the first part.

[0016] According to another feature, the second inner 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 fastening element configured to ensure at least partial transfer of the shear forces between the first and second parts, said second plate comprising a second flat and smooth face pressed against the second inner face of the second part.

[0017] According to another feature, each plate includes an extension through which at least one fixing element passes, having a thickness less than that of the rest of the plate.

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

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

[0020] According to another feature, the first and second striations are concentric circles around the stem of the connecting element.

[0021] According to another feature, the first and second striations have a height 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 includes a frame delimiting an opening, a removable panel configured to close the opening and at least one assembly linking 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 having respectively first and second transverse reinforcements pressed against each other and 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 having a first structure, a second structure and at least one assembly linking the first and second structures which correspond respectively to the first and second parts of the assembly.

[0026] The invention also relates to an assembly method comprising a step of positioning the first and second plates between the first and second parts, at least one of them not being fixed 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 putting in place at least one connecting element, the first and second grooves interlocking with each other during this placement, a step of fixing the first and second plates, not yet fixed, respectively to the first and second parts,Each of the first and second plates is secured to the first or second part by at least one fastening element configured to ensure at least partial transmission of shear forces between the first and second parts.

[0027] According to another feature, the first and second grooves are configured according to the deformations of the first and second parts during disassembly in order to catch up with said deformations during reassembly.

[0028] According to another feature, 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 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:

[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 an embodiment of the invention,

[0032] [Fig.3] is a front view of part of a contact surface illustrating a mode of the realization of the invention,

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

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

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

[0036] [Fig.7] is a cross-section of a part of the demountable and fixed structures visible in [Fig. 6], linked 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 an embodiment of the invention,

[0040] [Fig. 11] is a front view of an assembly connecting two fuselage sections illustrating one 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 central wing box structures 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 plates illustrating an embodiment of the invention, before clamping on part (A) and after clamping on part (B).

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

[0047] Around the first through-hole 22.3, the first internal and external faces 22.1, 22.2 are substantially flat and parallel to each other. The first through-hole 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 inner and outer 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 inner and outer faces 24.1, 24.2.

[0049] The assembly 20 includes at least one connecting element 26 linking the first and second parts 22, 24, comprising a rod 28 positioned in the through holes 22.3, 24.3 and first and second stops 30.1, 30.2 linked 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 includes 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 made independently of each other, prior to assembly. Thus, the first and second parts 22, 24 are not drilled simultaneously during assembly, and the assembly process does not include a drilling step. This solution simplifies assembly insofar as the first and second through holes 22.3, 24.3 can be made before the assembly of the first and second parts 22, 24.

[0054] According to one configuration, the assembly 20 includes 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 connecting element 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. Regardless of the embodiment, each connecting element 26 comprises a rod 28 configured to ensure the transfer of tensile / compressive forces between the first and second parts 22, 24.

[0056] The assembly also includes 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 the level of a contact plane P, so that the first and second grooves S32, S34 are interlocked with 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 striae, we mean an alternating succession of grooves (recessed) and ribs (protruding).

[0058] The first and second grooves S32, S34 are configured to ensure the 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 gap 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 grooves as shapes for ensuring the 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 interlock with 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 transfer of tensile / compressive forces is separated from the transfer of shear forces, each being ensured by distinct elements, namely the connecting element 26 for tensile / compressive forces and the pair of first and second contact surfaces 32, 34 equipped with asperities for shear forces. Therefore, it is possible to optimize the dimensioning of the connecting element 26 for resisting tensile / compressive forces (without taking into account shear forces) as well as the dimensioning of the first and second grooves S32, S34 for resisting shear forces (without taking into account tensile / compressive forces).

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

[0061] According to a second configuration visible on [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 for omnidirectional shear force transfer.

[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 planes forming an angle of between 10 and 45° with respect to a line perpendicular to the inner 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 ribbed contact surface 32, 34 corresponds to the inner 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 inner 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 having 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 having 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 has at least one through hole 36.1 to accommodate the rod 28 of a connecting element 26. This arrangement allows the plate 36, through which the connecting element 26 passes, to be held in place before tightening.

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

[0067] Each fastener 40 comprises a rod having a cross-section determined by the shear forces to be transmitted. For example, each fastener 40 is a pin, a screw, or a shear rivet. For each fastener 40, the plate 36 and the first fastener each comprise a housing, such as a through hole, configured to accommodate the rod of the fastener 40. This housing has a cross-section adjusted to that of the rod of the fastener 40. As an indication, a clearance of approximately 0.1 to 0.2 mm is provided between the wall of each housing and the rod of the fastener 40 to allow the fastener 40 to be inserted into the housing. Alternatively, the fastener 40 could be press-fitted into its housing.

[0068] According to an embodiment shown in [Fig. 2], the assembly 20 comprises first and second plates 36, 38, interposed between the first and second inner 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 having 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 have at least one through hole 36.1, 38.1 to accommodate the rod 28 of a connecting element 26.

[0069] According to one configuration, the first inner 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 fastening element 40 and comprises a first flat and smooth face 36.2 pressed against the first inner 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 inner 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 includes a second flat and smooth face 38.2 pressed against the second internal face 24.1 of the second part 24 and 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 the transfer of 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 dimensioned according to the shear forces 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 joining a plate and a part. Alternatively, the first or second plate 36, 38 could be bonded or welded to the first or second part 22, 24. A first or second plate 36, 38 can be connected to the first or second part 22, 24 by one or more fastening elements 40, 42. Regardless of 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-hole 36.1, 38.1. In this case, the plate 36, 38 is traversed by a single connecting element 26. According to another embodiment shown in [Fig. 10], each plate 36, 38 comprises several through-holes 36.1, 38.1. In this case, the plate 36, 38 is traversed by several connecting elements 26.

[0072] According to an embodiment visible in [Fig.2], the first and second plates 36, 38 are projecting 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 the [Fig.

[11] , at least one of the first and second parts 22, 24 includes at least one recess 44 in relation to the first or second inner 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 recess 44 has a contour 44.1 substantially equal to that of at least one of the first and second plates 36, 38. The recess 44 has a depth (dimension taken perpendicular to the first or second inner 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 includes a first recess 44 configured to house the first plate 36 and the second part 24 includes a second recess configured to house the second plate 38. According to another configuration visible in [Fig.[l 1], only the first part 22 includes a housing configured to accommodate 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 transfer of shear forces between the plate 36, 38 and the first or second piece 22, 24 in which the housing 44 is provided.

[0075] As illustrated in [Fig.12], each plate 36, 38 includes an extension 46 (which does not cooperate with the other plate) through which at least one fixing element 40, 42 passes. 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 the initial assembly, the first plate 36 is connected to the first part 22 by means of a first fastening element 40. Then, the second plate 38, not connected to the second part 24, is positioned relative to the first plate 36 and held in place by a temporary connection, such as adhesive. Next, the second part 24 is positioned relative to the second plate 38 and connected to it by means of a second fastening element 42. Finally, the connecting element 26 is put in place and tightened.

[0077] According to one method, an assembly process 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 attached 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 installing at least one connecting element 26, during this installation, the first and second grooves S32, S34 interlocking with each other; a step of fixing the first and second plates 36, 38, not yet attached, respectively to the first and second parts 22, 24, each of the first and second plates 36, 38 being attached to the first or second part 22, 24 by at least one element 40 fixing points,42 configured to ensure at least partial transmission of 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 and 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 and 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 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 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 straight and parallel to each other.

[0083] The fuselage 52 includes an outer wall 64 forming the skin of the aircraft 50. According to an arrangement, each assembly 20 has a contact plane P which forms an angle of approximately 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' comprise respectively 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 sector of a ring which has the same radius of curvature as the first or second transverse reinforcement 66, 66' to which it is connected. In 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 and at least one assembly 20 linking 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 and 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 on either side of the first panel 70.1. The first brackets 70.2, 70.3 have coplanar SI junction surfaces.

[0089] The second structure 72 comprises at least one second panel 72.1 and 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 coplanar second 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 joining surface SI, the second plate 38 of each pair being connected to a second bracket 72.2, 72.3.

[0091] The assembly 20 can include one or more pair(s) of first or second plate(s) 36, 38, each of the first and second plate(s) 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 through one or more connecting element(s) 26.

[0092] According to an arrangement visible on [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 dimensioned to ensure the transfer of shear forces, and a second series of first and second grooves S32', S34' configured to ensure the repositioning of the first and second parts 22, 24 relative to each other and the transfer 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 first or second grooves S32, S34 are identical and are configured to ensure repositioning of the first and second parts 22, 24 relative to each other and a resumption of shear forces. Regardless of the variant, the first and second grooves 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 subsequent reassemblies.

[0096] According to one procedure, during disassembly and until reassembly, the first and second plates 36, 38 remain attached to the first and second parts 22, 24, respectively. During reassembly, the first and second grooves S32', S34' are positioned so that the same grooves S32', S34' cooperate with each other as during the initial assembly. As illustrated in part (A) of [Fig. 16], since the grooves S32', S34' are not fully interlocked, the first and second parts 22, 24 may shift relative to each other. When the connecting element 26 (or connecting elements 26) is tightened, the grooves S32', S34' interlock with each other. Due to the inclined faces 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 initial assembly, the grooves S32, S34 are oriented according to the displacement DI to be made between the first and second parts 22, 24 to compensate for the deformation of at least one of them during disassembly. If the first and second parts 22, 24 tend to deform along a direction DI during disassembly and a displacement along the opposite direction DI between the first and second parts 22, 24 is necessary during reassembly, the grooves S32, S34 are oriented during the initial assembly so that their crests are perpendicular to the direction DI.

[0098] When first and second parts 22, 24 are large, the first and second grooves S32, S34 of the assembly are not necessarily all oriented in the same way. If a first area of ​​one of the parts 22, 24 tends to deform in a first direction, the first and second grooves S32, S34 present in this first area will be oriented perpendicular to this first direction. If a second area of ​​one of the parts 22, 24 tends to deform in a second direction (intersecting the first direction), the first and second grooves S32, S34 in this second area will be oriented perpendicular to the second direction.

[0099] According to one operating method, during initial assembly, the first and second grooves S32, S34 are configured not only according to shear forces to be transmitted between the first and second parts 22, 24, but also according to 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 in at least one 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 differently from one area to another, the first and second grooves S32, S34 are configured, during a first assembly, area by area according to the deformations of the first and second parts 22, 24 during disassembly.

Claims

1. Demands Assembly comprising at least first and second parts (22, 24) and 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), 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); the assembly (20) comprising 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), each plate (36, 38) having at least one through hole (36.1) to accommodate the rod (28) of the connecting element (26); characterized in that the first internal face (22.1) of the first part (22) is flat and smooth, in that the first plate (36) is connected to the first part (22) by at least one first fastening element (40) configured to ensure at least partial transfer of 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), in that the second internal face (24.1) of the second part (24) is flat and smooth, in that the second plate (38) is connected to the second part (24) by at least one second fastening element (42) configured to ensure at least partial transfer of 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), and 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 provided with first asperities, the second contact surface (34) being provided with second asperities, the first and second plates (36, 38) comprising respectively the first and second contact surfaces (32, 34) provided with the first and second. asperities, the first and second asperities having complementary shapes configured to interlock with each other and ensure transmission of shear forces between the first and second pieces (22, 24).

2. Assembly according to the preceding claim, characterized in that each plate (36, 38) comprises an extension (46) through which at least one fixing element (40, 42) passes, having a thickness less than that of the rest of the plate (36, 38).

3. Assembly according to any one of the preceding claims, characterized in that at least one part among the first and second parts (22, 24) comprises at least one recess (44) in relation to the first or second inner 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).

4. Assembly according to any one of the preceding claims, characterized in that the first and second asperities are respectively first and second striations (S32, S34).

5. Assembly according to the preceding claim, characterized in that the first and second grooves (S32, S34) are straight and parallel to each other and oriented in a direction perpendicular to a direction of resumption of shear forces.

6. Assembly according to claim 4, characterized in that the first and second grooves (S32, S34) are concentric circles around the stem (28) of the connecting element (26).

7. Assembly according to any one of claims 4 to 6, characterized in that the first and second grooves (S32, S34) have a height between 1 and 5 mm.

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

9. 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) and at least one assembly (20) according to any one of claims 1 to 12 linking the frame (60) and the panel (62) which correspond respectively to the first and second parts (22, 24) of the assembly (20).

10. Aircraft according to claim 8, characterized in that the aircraft comprises at least two fuselage sections (58, 58') comprising respectively of the first and second transverse reinforcements (66, 66') pressed against each other and at least one assembly (20) according to any one of claims 1 to 12 linking the first and second transverse reinforcements (66, 66') which correspond respectively to the first and second parts (22, 24) of the assembly.

11. Aircraft according to claim 8, characterized in that the aircraft comprises a central wing box (56) having a first structure (70), a second structure (72) and at least one assembly (20) according to any one of claims 1 to 12 linking the first and second structures (70, 72) which correspond respectively to the first and second parts (22, 24) of the assembly (20).

12. A method for assembling an assembly according to any one of claims 1 to 7, characterized in that an assembly 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 attached 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 installing at least one connecting element (26), the first and second grooves (S32, S34) interlocking with each other during this installation, a step of fixing the first and second plates (36, 38), not yet attached, 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 fastening element (40, 42) configured to ensure at least partial transmission of shear forces between the first and second parts (22, 24).

13. Assembly 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 catch up with said deformations during reassembly.

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

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