Device for sealing connection between wing box and central fuselage of aircraft, corresponding sealing process and corresponding aircraft

Abstract

The invention relates to a device (1) for sealing a connection (93) between a wall (911) of a wing box (91) and a wall (921) of a central fuselage (92) of an aircraft, said device comprising at least one deformable element (11) clamped between a first rigid end element (13) and a second rigid end element (15). The apparatus further comprises clamping means (17) for moving the first rigid end element and the second rigid end element close to each other in order to deform the at least one deformable element by pressing until it presses against the wall of the connection. Such a device makes it possible to ensure the sealing of the connection while enabling simple and easy installation from the outside of the aircraft. Such a device can be easily adapted to different shapes of the connection to be sealed.

Description

Technical Field

[0001] The invention relates to a device for sealing a joint between a wing box and a center fuselage of an aircraft, in particular for sealing a fuel tank formed in the wing box, a process for sealing such a joint and an aircraft having at least one such sealing device. Background Art

[0002] It is known practice to use the wing box of the aircraft to form the fuel tank. However, such a solution requires a perfect seal at the junction between the wing box and the center fuselage of the aircraft to form the fuel tank. In fact, the assembly of the parts of the wing box and the parts of the center fuselage at this junction creates many openings that must be sealed to avoid fuel leaks.

[0003] A known technique for sealing the joint between the wing box and the center fuselage of an aircraft consists in injecting a sealing product containing small foam particles into these openings. To do this, the operator must first place a blocking element at each of the openings left between the wing and the center fuselage, which ensures that the sealing product can flow in a single direction when injected. Then, they must position an adhesive element for introducing the sealing product, which has a hole to receive the injection nozzle of a gun for injecting the sealing product, which can guide the sealing product toward the inside of the opening. Finally, the operator can use the injection gun to inject the sealing product into the opening.

[0004] One disadvantage of this technique is that the sealing product must be injected by the operator via the inside of the wing box. However, the space inside the wing box is very limited and the opening to be blocked with the sealing product is difficult for the operators to reach and they must therefore inject the product in a very uncomfortable position. Furthermore, in recent years, the height of the wings has been reduced in order to improve the performance of the wings of aircraft. The risk is that the technique is therefore increasingly complex to implement and that the ergonomic problems for the operator increase significantly. Therefore, this technique is not satisfactory.

[0005] Therefore, there is a need to provide a solution for sealing the joint between a wing box and a center fuselage of an aircraft which at least partially overcomes the drawbacks described with respect to the prior art. Summary of the invention

[0006] One object of the present invention is to propose a device for sealing a joint between at least one wall of a wing box of an aircraft and at least one wall of a central fuselage of said aircraft that is reliable and easy to implement.

[0007] To this end, a sealing device is proposed, which includes:

[0008] - at least one deformable element having a first hole, the at least one deformable element being intended to be arranged in the junction between at least one wall of the wing box and at least one wall of the central fuselage of the aircraft;

[0009] a first rigid end element having a second hole and a second rigid end element having a third hole, said second hole and the third hole extending coaxially with the first hole, said first and second rigid end elements being arranged on either side of said at least one deformable element and intended to clamp said at least one deformable element; and

[0010] - A clamping device having a nut and a clamping screw, the nut having a tapped portion and being arranged to abut against one of the rigid end elements, the clamping screw having a screw head and a threaded shank, the screw head being arranged to abut against the other of the rigid end elements, and the threaded shank being fitted in the first, second and third holes so as to be screwed to the nut.

[0011] The clamping device is movable between an inactive position, in which the clamping device does not clamp the first rigid end element and the second rigid end element towards each other and leaves the at least one deformable element in an undeformed initial position, and a clamping position, in which the clamping element deforms the at least one deformable element by squeezing until the at least one deformable element is intended to press against at least one wall of the wing box and / or against at least one wall of the center fuselage, thereby clamping the first rigid end element and the second rigid end element towards each other.

[0012] The rigid end element against which the nut is arranged to abut has a recess for receiving and retaining the nut, the recess preventing the nut from rotating relative to the rigid end element during clamping and loosening of the clamping device.

[0013] The device also includes a sealing product, which is intended to be arranged in the connection between at least one wall of the wing box and at least one wall of the central fuselage, and the sealing product is configured to block the space left between the at least one deformable element and at least one wall of the wing box and / or at least one wall of the central fuselage.

[0014] Such a sealing device can ensure the sealing of the joint while enabling simple and easy installation from the outside of the aircraft. In addition, such a device can be easily adapted to different shapes of the joint to be sealed.

[0015] Advantageously, said device comprises a sealing product arranged to at least partially surround said at least one deformable element, at least when said clamping means of said device are in said clamping position, said sealing product being configured to block a space left between said at least one deformable element and at least one wall of said wing box and / or at least one wall of said center fuselage.

[0016] According to a specific exemplary embodiment of the present invention, the at least one deformable element has at least one deformable cavity containing the sealing product, the at least one deformable cavity is connected to the outside of the at least one deformable element through at least one channel, and the at least one deformable cavity has an internal volume, which becomes smaller during clamping by the clamping device to force the sealing product to flow to the outside of the at least one deformable element.

[0017] According to a specific aspect of the present invention, the sealing device also includes at least one intermediate rigid element. When the device has multiple deformable elements, the at least one intermediate rigid element is arranged in the at least one deformable element or between at least two deformable elements. The at least one intermediate rigid element has a fourth hole extending coaxially with the first hole, and the threaded handle is assembled in the fourth hole.

[0018] According to another aspect of the present invention, the at least one intermediate rigid element has a polygonal cross-section, the at least one deformable element has a recessed portion with a cross-section having a shape complementary to that of the at least one intermediate rigid element, or the at least two deformable elements receive the at least one intermediate rigid element, and the at least two deformable elements have faces with a shape complementary to that of the at least one intermediate rigid element.

[0019] According to an exemplary embodiment, the invention also proposes a process for sealing a joint between at least one wall of a wing box of an aircraft and at least one wall of a central fuselage of the aircraft, the process comprising the following steps:

[0020] - introducing a sealing product between at least one wall of the wing box and at least one wall of the central fuselage;

[0021] - providing the equipment as described above;

[0022] - inserting and positioning the sealing device in the joint between at least one wall of the wing box and at least one wall of the central fuselage of the aircraft; and

[0023] - Clamping the clamping device from the inactive position into the clamping position.

[0024] According to another exemplary embodiment, the invention proposes a process for sealing a joint between at least one wall of a wing box of an aircraft and at least one wall of a central fuselage of the aircraft, the process comprising the following steps:

[0025] - providing the equipment as described above;

[0026] - inserting and positioning the sealing device in the joint between at least one wall of the wing box and at least one wall of the central fuselage of the aircraft; and

[0027] - Clamping the clamping device from the inactive position into the clamping position.

[0028] According to one aspect of this another exemplary embodiment, the step of providing the sealing device comprises the following sub-steps:

[0029] - providing at least one deformable element having at least one cavity;

[0030] - injecting a sealing product into at least one cavity of said at least one deformable element; and

[0031] - Assembling said first rigid end element and said second rigid end unit on each side of said at least one deformable element and on said clamping means.

[0032] The invention also proposes an aircraft comprising a wing box having at least one wall, a central fuselage having at least one wall and at least one sealing device as described above, arranged between at least one wall of the wing box and at least one wall of the central fuselage. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] The above and other features of the present invention will become more apparent upon reading the following description of several exemplary embodiments, which description is given with reference to the accompanying drawings, in which:

[0034] Figure 1 is a top view of an aircraft implementing a plurality of sealing devices according to the present invention;

[0035] Figure 2 is a side cross-sectional view of a sealing device according to a first embodiment of the present invention, with a clamping device of the sealing device in an inactive position;

[0036] Figure 3 yes Figure 2 A side cross-sectional view of the sealing device in FIG. 1 , wherein the clamping device of the sealing device is in a clamping position;

[0037] Figure 4is a side cross-sectional view of the connection between the wing box and the center fuselage of an aircraft before the sealing device according to the invention is installed;

[0038] Figure 5 Is installing Figure 2 After the sealing device, according to Figure 4 A side cross-sectional view of a connection between a wing box and a center fuselage of an aircraft;

[0039] Figure 6 Schematically shows the implementation Figure 2 The steps of the sealing process of the sealing device;

[0040] Figure 7 is a side cross-sectional view of a sealing device according to a second embodiment of the present invention, with a clamping device of the sealing device in an inactive position;

[0041] Figure 8 yes Figure 7 A side cross-sectional view of the sealing device in FIG. 1 , wherein the clamping device of the sealing device is in a clamping position;

[0042] Fig. 9 yes Figure 7 A side cross-sectional view of a variation of the sealing device in FIG. 1 , wherein the clamping device of the sealing device is in an inactive position;

[0043] Fig.10 yes Fig. 9 A side cross-sectional view of the sealing device in FIG. 1 , wherein the clamping device of the sealing device is in a clamping position;

[0044] Fig.11 Schematically shows the implementation Figure 7 or Fig. 9 The steps of the sealing process of the sealing device;

[0045] Fig.12 Schematically shows Fig.11 A sub-step of one of the steps of the sealing process;

[0046] Fig.13 Shows Fig.12 A sub-step in the sealing process;

[0047] Fig.14 Shows Fig.12 Another sub-step of the sealing process in; and

[0048] Fig.15 Shows Fig.11 A step in the sealing process. DETAILED DESCRIPTION

[0049] Figure 1An aircraft 9 is shown, comprising a central fuselage 92 and two wing boxes 91, in particular a port and a starboard wing box, each of which is joined to the central fuselage 92 at a joint 93. When the wing boxes 91 of the aircraft 9 are used to form fuel tanks, it is necessary to ensure a perfect sealing of the joint 93 between the wing boxes 91 and the central fuselage 92. To this end, the invention implements a sealing device 1, 1' which ensures an optimal sealing of the joint 93 while making it easier to install, such installation preferably being able to be carried out via the outside of the aircraft 9. The sealing device 1, 1' is intended to be implemented between at least one wall 911 of the wing box 91 and at least one wall 921 of the central fuselage 92 (as shown in the following figures).

[0050] Figures 2 to 5 A first embodiment of a sealing device 1 is shown for sealing a joint 93 between a wing box 91 and a central fuselage 92 of an aircraft 9 , and in particular in the present case a joint 93 between a wall 911 of the wing box 91 and a wall 921 of the central fuselage 92 .

[0051] The sealing device 1 comprises a first rigid end element 13 and a second rigid end element 15, which respectively have a first hole 131 and a second hole 151 extending coaxially. One of the rigid end elements 13 and 15 has a recess 153 for receiving and retaining a nut 171 described below. The recess 153 extends coaxially with the first hole 131 and the second hole 151.

[0052] The geometry of the rigid end elements 13 and 15 depends on the geometry of the cross section of the cavity to be sealed. For example, if the cavity has a circular cross section, the rigid end elements 13 and 15 preferably have the general form of a gasket, while if the cavity has a rectangular cross section, the rigid end elements 13 and 15 also preferably have a rectangular shape. The rigid end elements 13 and 15 are for example made of metal or a rigid plastic that is slightly deformable or non-deformable so as to allow optimal transmission of the clamping force from the clamping device 17 on the at least one deformable element 11 (described below).

[0053] The rigid end elements 13 and 15 are arranged on each side of at least one deformable element 11 and are intended to clamp the one or more deformable elements. In the example shown, the sealing device 1 comprises two deformable elements 11, which are arranged adjacent to each other or in series between the rigid end elements 13 and 15. The rest of the description is based on this example, but it will be easily understood that the description can be applied to sealing devices 1 implementing only one deformable element 1 or to sealing devices 1 implementing a greater number of deformable elements.

[0054] Each deformable element 11 has a main hole 111 extending coaxially with the first hole 131 and the second hole 151 of the rigid end elements 13 and 15 .

[0055] The deformable element 11 is intended to be deformed by contact with the wall 911 of the wing box 91 and the wall 921 of the central fuselage 92, and more particularly by pressing against them, to ensure the sealing of the joint 93. Preferably, and in order to ensure an optimal and stable deformation and return to the initial position, the deformable element 11 is made of an elastomer.

[0056] The implementation of a plurality of deformable elements 11 makes it possible in particular to adapt optimally to the shape of the spaces left between the walls 911 of the wing box 91 and the walls 921 of the central fuselage 92 , since these spaces can sometimes have a complex and variable shape.

[0057] The sealing device 1 further comprises a clamping device 17 having a nut 171 and a clamping screw 173. The nut 171 has a tapped portion 1711 extending coaxially with the main hole 111. The nut 171 is arranged to abut against one of the rigid end elements 13 and 15. More specifically, the nut 171 is positioned in a recess 153 formed in one of the rigid end elements 13 and 15 to prevent its rotation during clamping by the clamping device 17. In this example, the recess 153 is formed in the second rigid end element 15.

[0058] The clamping screw 173 has a screw head 175 and a threaded shank 177. The screw head 175 is arranged to abut against the other of the rigid end elements 15 and 13 (in this example specifically against the first rigid end element 13), while the threaded shank 177 is successively fitted in the first hole 131, the main hole 111 and the second hole 151 so as to be screwed into the tapped portion 1711 of the nut 171.

[0059] The clamping device 17 is movable between an inactive position and a clamping position. The clamping position depends in particular on the clamping force exerted on the clamping device 17.

[0060] In an inactive position (such as Figure 2 In the inactive position, the clamping device 17 does not clamp the first rigid end element 13 and the second rigid end element 15 towards each other and thus leaves the deformable element 11 in an undeformed initial position. In a variant embodiment, it is conceivable that, in the inactive position, the clamping device 17 exerts a weak clamping force so as to keep the deformable elements 11 under tension but not to deform them.

[0061] In the clamping position (such as Figure 3), the clamping device 17 clamps the first rigid end element 13 and the second rigid end element 15 toward each other. The clamping of the rigid end elements 13 and 15 toward each other can deform the deformable element 11 by squeezing. The clamping of the rigid end elements 13 and 15 toward each other can preferably deform the deformable element 11 until the outer surfaces of these deformable elements are pressed against the wall 911 of the wing box 91 and the wall 921 of the center fuselage 92, thereby sealing the joint 93.

[0062] Since the sealing device 1 includes a sealing product 2 (described in detail below), the outer surface of the deformable element 11 may not be in direct contact with the wall 911 of the wing box 91 and / or the wall 921 of the central fuselage 92. In particular, it is conceivable that the sealing product 2 is interposed between the deformable element 11 and one and / or the other of the walls 911 and 912. In a particular case, the sealing product 2 completely surrounds the deformable elements 11 of the sealing device 1, so that these deformable elements are not in direct contact with the wall 911 of the wing box 91 and / or the wall 921 of the central fuselage 92.

[0063] The rigid end elements 13 and 15 make it possible to hold the elements of the sealing device 1 together using the clamping device 17, in particular to hold them together before clamping by the clamping device 17, and to apply the compressive force generated during clamping by the clamping device to the deformable element 11, thereby deforming the deformable element by squeezing.

[0064] In order to make the rest of the description easier to understand, it will be understood that the inactive position of the clamping means 17 corresponds to the inactive position of the sealing device 1 , whereas the clamping position of the clamping means 17 corresponds to the clamping position of the sealing device 1 .

[0065] Optionally, when the sealing device 1 comprises a plurality of deformable elements 11, the sealing device 1 may comprise at least one intermediate rigid element 19, which is arranged inside the deformable element 11, or Figure 2 and Figure 3 As shown in the example in FIG. 1 , it is arranged between at least two deformable elements 11. The intermediate rigid element 19 has a third hole 191 extending coaxially with the main hole 111, and the threaded shank 177 of the clamping device 17 is assembled in the third hole 191.

[0066] In the present example, the sealing device 1 comprises an intermediate rigid element 19 arranged between two deformable elements 11. The intermediate rigid element 19 has in this case the general shape of a parallelepiped and separates the two deformable elements 11.

[0067] Implementing an intermediate rigid element 19 ensures optimal maintenance of the overall shape of the sealing device 1 and better transmission of the clamping forces from the clamping means 17 towards the deformable element or elements 11. The intermediate rigid element 19 also makes it possible to arrange identical deformable elements 11 (which are therefore manufactured using the same mould) in series on the clamping screw 173, in order to adapt to cavities with different lengths.

[0068] The sealing device 1 also includes a sealing product 2 ( Figure 2 and Figure 3 ), at least when the clamping device 17 of the sealing device 1 is in the clamping position, the sealing product 2 is at least partially arranged around the deformable element 11. The sealing product 2 is configured to block the space left between the deformable element 11 and the wall 911 of the wing box 91 and / or the wall 921 of the center fuselage 92 when the sealing device 1 is in the clamping position.

[0069] The sealing product 2 is, for example, of a mastic type, in particular a filling mastic type.

[0070] Figures 4 to 6 The use of the sealing device 1 in a process 81 for sealing a joint 93 between at least one wall 911 of a wing box 91 and at least one wall 921 of a central fuselage 92 is shown. In the example shown, the joint 93 to be sealed is between the wall 911 of the wing box 91 and the central fuselage 92, which in this case has two walls in the form of a structural element 921 of a door of the aircraft and a front vertical profile 923, respectively. The joint 93 also has a gasket 931, which extends partly between the front vertical profile 923 and a corner joint 932 and partly between the wall 911 of the wing box 91 and the corner joint 932.

[0071] The sealing process 81 , which is preferably carried out from the outside of the aircraft 9 , comprises the following steps:

[0072] - introducing 811 the sealing product into the joint 93, specifically, in this case, between at least one wall 911 of the wing box 91 and at least one wall 921 of the central fuselage 92, and more specifically, in this case, into the space left between the wall 911 of the wing box 91 and the walls 921, 923 of the fuselage 92;

[0073] - Provide 813 as above about Figure 2 and Figure 3 The sealing device 1;

[0074] - inserting and positioning 815 the sealing device 1 in the joint 93 , specifically in this case between the wing box 91 and the fuselage 92 (and more specifically in this case between the wall 911 of the wing box 91 and the two walls 921 , 923 of the central fuselage 92 );

[0075] - Clamping 817 the clamping device 17 from the inactive position to the clamping position.

[0076] exist Figure 4 and Figure 5 In the example shown, the introduction 811 of the sealing product 2 is carried out in the space left between the wing box 91 and the fuselage 92, this introduction 211 using a corner joint 932 with a gasket 931 which at least partially covers the junction 93 between the wing box 91 and the central fuselage 92. This introduction 811 of the sealing product 2 allows the sealing product 2 to diffuse, that is to say flow, around the deformable element 11 of the sealing device 1 once it is positioned in the junction 93, before the device 1 is inserted into the junction 93. After the clamping of the clamping means 17 for deforming and possibly for pressing the deformable element 11 against the walls 911 of the wing box 91 and the walls 921, 923 of the fuselage 92, the sealing product 2 present around the deformable element 11 in the junction 93 will make it possible to block any space left between the deformable element 11 and the walls 911 of the wing box 91 and / or the walls 921, 923 of the central fuselage 92.

[0077] Figure 7 and Figure 8 A second embodiment of a sealing device 1' for sealing a joint 93 between a wing 91 and a central fuselage 92 of an aircraft 9 is shown. As shown in this example, the sealing device 1' is arranged at the joint 93, in this case between the wall 911 of the wing box 91 and the wall 921 of the central fuselage 92. Figure 7 The sealing device 1 ′ is shown in its inactive position, while Figure 8 The sealing device 1 ′ is shown in its clamped position.

[0078] According to the first embodiment, the sealing device 1 ' according to the second embodiment comprises at least one deformable element 11, a first rigid end element 13 and a second rigid end element 15 and a clamping device 17. These elements have substantially the same structure and function as the elements of the first embodiment and are therefore not described in detail. Therefore, the same elements have the same reference numerals.

[0079] In the example shown, the second rigid end element 15, against which the nut 171 is arranged, has a recess 153 for receiving and retaining the nut 171, the recess 153 having a shape corresponding to the nut 171, so that the nut 171 engages with the second rigid end element 15 to avoid rotation of the nut 171 during clamping of the clamping device 17. In this way, the clamping device 17 can be clamped in particular from the outside of the aircraft.

[0080] The second embodiment differs from the first embodiment in that the sealing product 2 is contained in one or more deformable elements 11 before the sealing device 1 ′ is inserted into the connecting portion 93 and, therefore, is released from the one or more deformable elements 11 during clamping by the clamping device 17 .

[0081] To this end, at least one of the at least one deformable element 11 has at least one deformable cavity 113 containing the sealing product 2. The cavity 113 is deformable in the sense that the internal volume of the cavity 113 decreases during the clamping of the clamping device 17. Each cavity 113 is connected to the exterior 115 of the deformable element 11 in which the cavity 113 is located by at least one channel 117. It is also conceivable that the cavities 113 are interconnected.

[0082] In the illustrated example, the sealing device 1 ′ has only one deformable element 11 having a single cavity 113 connected to the outside of the deformable element by a plurality of channels 117. The remainder of the present description is based on this example, but it will be readily understood that the present description can be applied to sealing devices 1 implementing a greater number of deformable elements 11 and / or cavities 113.

[0083] When the clamping device 17 is moved from the inactive position ( Figure 7 ) moves to the clamping position ( Figure 8 ), the volume of the cavity 113 will become smaller, thus forcing the sealing product 2 to flow out of the cavity 113 through the one or more channels 117 to be distributed around the deformable element 11. In this way, when the sealing device 1 ' is in the clamping position, the sealing product 2 is arranged around the deformable element 11, thus blocking any space left between the deformable element 11 and the wall 911 of the wing box 91 and / or the wall 921 of the center fuselage 92.

[0084] Thus, the cavity 113 can contain the sealing product 2 within the deformable element 11 before the clamping of the clamping device 17, and release the sealing product 2 during the clamping of the clamping device 17 to ensure an optimal seal of the joint 93. The viscosity of the sealing product 2 is preferably selected so that the sealing product 2 cannot flow out of the cavity 113 through the channel 177 before the clamping of the clamping device 17. As a result, the sealing product 2 remains in the cavity 113 even when the device 1 'is positioned in the joint 93, as described below.

[0085] In a variant of the second embodiment, the sealing device 1 ′ comprises at least one intermediate rigid element 19 arranged inside the deformable element 11 or between at least two deformable elements 11. Fig. 9 and Fig.10In the example shown, the sealing device 1' comprises an intermediate rigid element 19 arranged in a deformable element 11 having two parts 11a, 11b. As mentioned above, the intermediate rigid element 19 has a fourth hole (not shown in these figures) in which the threaded shank 177 of the clamping device 17 fits.

[0086] The deformable element 11 receiving at least one intermediate rigid element 19 has a recess 119 with a cross section having a shape complementary to that of the at least one intermediate rigid element 19. When the sealing device 1 ′ comprises at least two deformable elements 11 receiving said at least one intermediate rigid element 19, the deformable elements 11 have a face with a shape complementary to that of said at least one intermediate rigid element 19.

[0087] In this example, the intermediate rigid element 19 has an octagonal overall shape and separates the two parts 11a, 11b of the deformable element 11. The faces of the two parts 11a, 11b that face each other and interact with the intermediate rigid element 19 when the sealing device 1 ' is in the inactive position each have a recess 119 with a shape corresponding to that of the intermediate rigid element 19.

[0088] In this variant, the sealing product 2 is contained in a cavity 113 formed between the two parts 11a, 11b of the deformable element 11. An intermediate rigid element 19 is arranged inside this cavity 113. A channel 117 allowing the sealing product 2 to flow out of the cavity is formed in this case at the intersection of the two parts 11a, 11b of the deformable element 11 and the intermediate rigid element 19.

[0089] In this variant, the implementation of an intermediate rigid element 19 may also provide optimal maintenance of the overall shape of the device 1' and better transmission of the clamping force from the clamping device 17 towards the deformable element 11, so as to ensure the desired deformation of the deformable element 11 and a controlled flow of the sealed product 2 towards the outside 115 of the deformable element 11.

[0090] Figures 11 to 15 The use of the sealing device 1 ′ in a process 82 for sealing a joint 93 between at least one wall 911 of a wing box 91 and at least one wall 921 of a centre fuselage 92 is shown.

[0091] The sealing process 82, which is preferably performed from the outside of the aircraft 9, comprises the following steps: Fig.11 :

[0092] - Provide 813 as above about Figures 7 to 10 Said sealing device 1';

[0093] - Insert the sealing device 1' into ( Fig.15 ) and locate ( Figure 7 and Fig. 9 ) 823 in the connection portion 93, that is, between at least one wall 911 of the wing box 91 and at least one wall 921 of the central fuselage 92;

[0094] - Clamping 825 the clamping device 17 from the inactive position into the clamping position ( Figure 8 and Fig.10 ).

[0095] The clamping step 825 consists in clamping the clamping means 17 until the at least one deformable element 11 is pressed against the at least one wall 911 of the wing box 91 and the at least one wall 921 of the center fuselage 92. The clamping 825 also allows the sealing product 2 contained in the one or more cavities 113 to flow out from the one or more cavities 113 towards the outside 115 of the sealing device 1 ', so as to block any space left between the one or more deformable elements 11 and the at least one wall 911 of the wing box 91 and / or the at least one wall 921 of the center fuselage 92.

[0096] The providing step 821 for providing the sealing device 1' comprises the following sub-steps (eg Fig.12 shown):

[0097] - providing 8211 at least one deformable element 11 having at least one cavity 113;

[0098] -Inject the sealing product 2 into 8213 ( Fig.13 ) into the at least one cavity 113 of the at least one deformable element 11;

[0099] - Assemble the first rigid end element 13 and the second rigid end element 15 8215 ( Fig.14 ) on each side of the at least one deformable element 11 and the clamping device 17.

[0100] In one variant, during the providing sub-step 8211 for providing at least one deformable element 11, one of the first rigid end element 13 and the second rigid end element 15 may already be connected to the at least one deformable element 11, in particular if they are rigid end elements 13, 15 that can close one or more cavities 113.

[0101] The injection sub-step 8213 for injecting the sealing product 2 into the at least one cavity 113 can be performed by the channel 117 (such as Fig.13 As shown), or if one or more cavities 113 are opened before assembling the rigid end members 13 and 15, injection can be performed directly into the one or more cavities 113.

[0102] It should be noted that the step of providing the sealing device 1, 1' (813 in the first embodiment and 821 in the second embodiment) is preferably carried out outside the aircraft 9, for example directly on a workbench near the aircraft 9, or in the factory of the supplier. Therefore, regardless of the geometry and size of the joint 93, it is possible to provide or manufacture a sealing device 1, 1' that is particularly adapted to the shape of the joint 93. In particular, the rigid end element and the deformable element or elements 11 can be adapted in shape and size to the opening of the joint 93 that must be sealed.

[0103] Preferably, the entire sealing process 81 , 82 is performed from outside the aircraft to limit ergonomic constraints and make the operator's job easier.

[0104] The sealing device 1 , 1 ′ of the invention makes it possible to implement a solid element in the opening of the joint 93 to be sealed, thereby forming a reliable and safe solution for sealing such a joint.

Claims

1. A sealing device (1, 1') intended for sealing a joint (93) between at least one wall (911) of a wing box (91) of an aircraft (9) and at least one wall (921) of a central fuselage (92) of the aircraft (9), the device (1, 1') comprising: - at least one deformable element (11) having a main hole (111), the at least one deformable element (11) being intended to be arranged in the joint (93) between at least one wall (911) of the wing box (91) and at least one wall (921) of the central fuselage (92) of the aircraft (9); - a first rigid end element (13) having a first hole (131) and a second rigid end element (15) having a second hole (151), said first hole (131) and said second hole (151) extending coaxially with said main hole (111), said rigid end elements (13, 15) being arranged on each side of said at least one deformable element (11) and intended to clamp said at least one deformable element (11); and - a clamping device (17), comprising a nut (171) having a tapped portion (1711) and arranged to abut against one of the rigid end elements (13, 15), and a clamping screw (173) having a screw head (175) and a threaded shank (177), the screw head (175) being arranged to abut against the other of the rigid end elements (15, 13), and the threaded shank (177) being fitted in the main hole (111) and in the first hole (131) and the second hole (151) so as to be screwed to the nut (171); wherein the clamping device (17) is movable between an inactive position and a clamping position, in which the clamping device (17) does not clamp the first rigid end element (13) and the second rigid end element (15) toward each other and leaves the at least one deformable element (11) in an undeformed initial position, and in which the clamping device (17) deforms the at least one deformable element (11) by squeezing until the at least one deformable element (11) is pressed against at least one wall (911) of the wing box (91) and / or against at least one wall (92) of the center fuselage (92), thereby clamping the first rigid end element (13) and the second rigid end element (15) toward each other; and wherein the rigid end element (13, 15) against which the nut (171) is arranged has a recess (153) for receiving and retaining the nut, the recess preventing the nut (171) from rotating relative to the rigid end element (13, 15) during clamping and loosening of the clamping device (17); The device (1, 1') also includes a sealing product (2), which is intended to be arranged in the connecting portion (93) between at least one wall (911) of the wing box (91) and at least one wall (921) of the central fuselage (92), and the sealing product (2) is configured to block the space left between the at least one deformable element (11) and at least one wall (911) of the wing box (91) and / or at least one wall (921) of the central fuselage (92).

2. The sealing device (1, 1') according to claim 1, characterized in that The device (1, 1') comprises a sealing product (2) arranged to at least partially surround the at least one deformable element (11) at least when the clamping means (17) of the device (1, 1') are in the clamping position.

3. The sealing device (1') according to claim 2, characterized in that The at least one deformable element (11) has at least one deformable cavity (113) containing the sealing product (2), and the at least one deformable cavity (113) is connected to the outside (115) of the at least one deformable element (11) through at least one channel (117). The at least one deformable cavity (113) has an internal volume, which becomes smaller during clamping by the clamping device (17) to force the sealing product (2) to flow to the outside (115) of the at least one deformable element (11).

4. The sealing device (1, 1') according to claim 1, characterized in that The sealing device (1, 1') also includes at least one intermediate rigid element (19). When the device (1, 1') has a plurality of deformable elements (11), the at least one intermediate rigid element is arranged in the at least one deformable element (11) or between at least two deformable elements (11), and the at least one intermediate rigid element (19) has a third hole (191) extending coaxially with the first hole (111), and the threaded stem (177) is assembled in the third hole.

5. The sealing device (1, 1') according to claim 4, characterized in that The at least one intermediate rigid element (19) has a polygonal cross-section, the at least one deformable element (11) has a recess (119) having a cross-section having a shape complementary to the at least one intermediate rigid element (19), or the at least two deformable elements (11) receive the at least one intermediate rigid element (19), and the at least two deformable elements have faces having a shape complementary to the at least one intermediate rigid element (19).

6. A sealing process (81) for sealing a joint (93) between at least one wall (911) of a wing box (91) of an aircraft (9) and at least one wall (921) of a central fuselage (92) of the aircraft (9), the sealing process comprising the following steps: - introducing (811) a sealing product (2) between at least one wall (911) of the wing box (91) and at least one wall (921) of the central fuselage (92); - providing (813) a sealing device (1) according to claim 1; - inserting and positioning (813) the sealing device (1) in the joint (93) between at least one wall (911) of the wing box (91) and at least one wall (921) of the central fuselage (92) of the aircraft (9); and - Clamping (815) the clamping device (17) from the inactive position into the clamping position.

7. A sealing process (82) for sealing a joint (93) between at least one wall (911) of a wing box (91) of an aircraft (9) and at least one wall (921) of a central fuselage (92) of the aircraft (9), the sealing process comprising the following steps: - providing (821) a sealing device (1') according to claim 3; - inserting and positioning (823) the sealing device (1') in the joint (93) between at least one wall (911) of the wing box (91) and at least one wall (921) of the central fuselage (92) of the aircraft (9); and - Clamping (825) the clamping device (17) from the inactive position into the clamping position.

8. The sealing process (82) according to claim 7, characterized in that: The providing step (821) for providing the sealing device (1') has the following sub-steps: - providing (8211) at least one deformable element (11) having at least one cavity (113); - injecting (8213) a sealing product (2) into at least one cavity (113) of said at least one deformable element (11); as well as - Assembling (8215) said first rigid end element (13) and said second rigid end unit (15) on the sides of said at least one deformable element (11) and on said clamping means (17).

9. An aircraft (9), comprising a wing box (91) having at least one wall (911), a central fuselage (92) having at least one wall (921), and at least one sealing device (1, 1') according to claim 1, the sealing device being arranged between at least one wall (911) of the wing box (91) and at least one wall (921) of the central fuselage (92).

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