Quick-attachment for a movable flap module of an aircraft wing

Description

TECHNICAL FIELD AND STATE OF THE PRIOR ART

[0001] The present invention relates to the field of aircraft wings, of the type comprising a central wing body which remains fixed and which carries one or more movable leading edge flaps, also called "slats".

[0002] Each of the two wings of the wing structure is generally equipped with high-lift flaps, mounted on the leading edge of the wing. The flaps are deployed for landing and takeoff to increase lift at low or medium speeds. In high-speed cruising flight, the flaps are retracted to limit the aircraft's resistance to forward movement.

[0003] Today, the assembly of fixed leading edges and movable flaps on the wing involves many operations. Fixed leading edges and movable flaps consist of a multitude of parts, including, for example, ribs, skins, electrical systems as well as guide rails, hinges and pivot arms, to allow the movable part to be imposed the desired movement. During the assembly of the fixed leading edges and movable flaps, these different parts are individually integrated into the wing by operations, among others, drilling and riveting to form the fixed leading edge and bolting and adjustment to mount the movable flaps. During this time, other work on the wing cannot be carried out and the assembly line remains blocked.Furthermore, drilling operations are likely to deposit metal shavings in removable parts of the wing which are thus at risk of being damaged during their movement.

[0004] Document US 2008 / 256788 A1 discloses a method of assembling parts to form an aircraft component, wherein a first surface of a first part, e.g., a wing skin, is to be positioned in the assembly adjacent a second surface of a second part, e.g., a rib root.

[0005] Thus, it would be advantageous to design a leading edge module, comprising the fixed leading edge, the movable flap with its removable parts, which are mounted on the wing without the need to carry out drilling operations on the assembly line. STATEMENT OF THE INVENTION

[0006] It is therefore an object of the present invention to provide a method of manufacturing a connecting part between a wing box and a leading edge module, the method comprising the steps according to claim 1.

[0007] The assembly of the first reference region, the second reference region and said relative position may be configured to uniquely determine a relative position between the wing box and the leading edge module.

[0008] It is also possible that the first reference region comprises a first device attached to the wing box and / or that the second reference region comprises a second device attached to the leading edge.

[0009] Advantageously, the connecting piece comprises an eccentric guide ring and the step of designing the connecting piece to provide a connection between the first and second connection regions comprises adapting at least one eccentricity of the ring to coincide an exterior of the ring with a first opening and an interior of the ring with a second opening, the first and second openings being located on the connection region.

[0010] Preferably the first reference region comprises an upper row of spar fasteners and / or a lower row of spar fasteners and / or a second reference region comprises an upper surface of the main rib.

[0011] Three-dimensional scanning may be performed by a 3D scanner or stereovision device.

[0012] The connecting part can be manufactured by a mechanical machining process or by a 3D printing process.

[0013] The invention also relates to an assembly according to claim 7.

[0014] In said set at least one distance measured on the first part may be different from the same distance measured on the second part, preferably the difference being 3% or more.

[0015] The invention also relates to an assembly formed of a first aircraft comprising a first wing, and a second aircraft equipped with a second wing, the first and second aircraft being of the same type, the first wing comprising a first leading edge module fixed to a first box of the first wing by a first connecting piece located at a position in the first wing, the second wing comprising a second leading edge module fixed to a second box of the second wing by a second connecting piece located at said position in the second wing, the two said connecting pieces each being a ring, the two said connecting pieces being manufactured according to the method described previously, the first connecting piece not being exchangeable with the second connecting piece. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The present invention will be better understood on the basis of the following description and the attached drawings in which: there figure 1 shows a fixed leading edge module and the forward part of a wing box of an aircraft wing, the figure 2shows the wing box comprising a first connection region, the figure 3 shows the leading edge module including a second connection region, the Figures 4a and 4b show a digital model and a plate as a connecting part, not covered by the present invention, the Figures 5a, 5b and 5c show a ring as a connecting piece, the Figures 6a, 6b and 6c show a multi-level plate as a connecting piece, not covered by the present invention, the figure 7 shows reference regions, the figure 8 shows steps in a process for manufacturing a connecting part. DETAILED DESCRIPTION OF SPECIFIC EMBODIMENTS

[0017] There figure 1 shows a fixed leading edge module 30 of the forward portion of a wing box 20 of a wing of an aircraft.

[0018] The wing box is delimited by a wing spar 500, an upper surface skin 510 and a lower surface skin 520. The wing box includes a first connection region 90, configured to mount the leading edge module. In the example shown in the figure 1 , the first connection region comprises eyelets 170.

[0019] The leading edge module 30 comprises, for its part, a second connection region 110, configured to allow the leading edge module to be fixed to the wing box. In the example shown, this also involves one or more eyelets.

[0020] There figure 8 shows a method of manufacturing a connecting part between the wing box 20 and the leading edge module 30, said part being provided for fixing the leading edge module to the wing box. The method will be explained subsequently using the figures 2 to 7 .

[0021] In a first step 410, a three-dimensional digitization of a first representative part of the wing box 40 is carried out in order to obtain a first digital model 50.

[0022] There figure 2shows the wing box 20 comprising the first connection region 90. A scanning device 290 is also shown. This may be, for example, a 3D three-dimensional scanner or a stereovision device. The scanning device is configured to perform the three-dimensional scanning of the first representative part of the wing box. Said representative part may, for example, be an interior of the wing box. In this case, the scanning device is, for example, oriented to obtain a digital model of the interior of the wing box. The first representative part comprises the first connection region 90 and a first reference region 80. Accordingly, a first digital model obtained from said scanning comprises the first connection region and the first reference region.

[0023] The first reference region is a visible part in the digital model having a fixed or temporarily fixed position relative to the first connection region. For example, as shown in the figure 2 , the first reference region 80 may be an upper edge and / or a lower edge of the wing box. In this case, said position is fixed. The first reference region may also be a line or a quarter located on a transport frame fixed to the wing box. In this case, said position is temporarily fixed, while the wing box remains in connection with the transport frame.

[0024] In a second step, a three-dimensional scanning of a second representative part of the leading edge module 60 is carried out in order to obtain a second digital model 70.

[0025] There figure 3shows the leading edge module 30 comprising the second connection region 110. The scanning device 290 is, in this case, oriented and configured to perform the three-dimensional scanning of the second representative part of the leading edge module. Similar to what has been described previously, the second representative part comprises the second connection region 110 and a second reference region 100. The second digital model thus comprises and shows the second connection region and the second reference region.

[0026] In the case shown in the figure 3, the second reference region is an interior of the leading edge module comprising an upper edge and / or a lower edge of the leading edge and / or a surface of the central rib. As described previously, the second reference region has a fixed or temporarily fixed position relative to the second connection region. For example, the second reference region may be located on a transport frame 140 of the leading edge module.

[0027] In a third step 430 a relative position 120 of the first reference region with respect to the second reference region is defined.

[0028] There Figure 4ashows the first digital model 50 of the wing box 20 and the second digital model 70 of the leading edge module 30. Since the digital models were obtained, using the scanning device 290, from manufactured parts, said models show possible manufacturing hazards. In other words, the relative dimensions of the two manufactured parts (the leading edge module and the particular wing box that was scanned) are represented by the respective digital models. The first digital model also includes the first reference region 80, located on the wing box, and the first connection region 90. The second digital model 70 includes the second reference region 100 and the second connection region 110.

[0029] The relative position 120 of the first reference region with respect to the second reference region may, for example, be a distance. The relative position 120 may also be a vector defined in a three-dimensional space. For example, said vector may be defined in a reference frame fixed to the wing box or fixed to the leading edge module. It is also possible to provide a plurality of first reference regions and / or a plurality of second reference regions and / or to define a plurality of associated relative positions. For example, as shown in the Figure 4a , two first reference regions and two second reference regions have been identified. In this case, two relative positions 120 are defined.

[0030] The first and second reference regions and said relative position are configured so as to obtain a relative position of the leading edge module and the wing box as intended for the construction of the wing of the aircraft.

[0031] Preferably, the assembly of the first reference region, the second reference region and said relative position is configured to uniquely determine a relative position between the wing box and the leading edge module.

[0032] Viewed from the wing box or from the leading edge module, the other part to be mounted has six degrees of freedom. In a Cartesian frame fixed on one of the two parts (the leading edge module or the wing box), the other part has three degrees of freedom in translation, in an x, y and z direction. The other part also has three degrees of freedom in rotation, around the x, y and z axis.

[0033] Preferably the assembly of the first reference region, the second reference region and said relative position is thus designed to determine said six degrees (three degrees of translation and three degrees of rotation) of freedom of the leading edge module relative to the wing box, or vice versa.

[0034] In a fourth step 440, the connecting part 10 is designed from the first and second digital models, the models placed in the relative position as defined in the third step, described above.

[0035] The connecting piece is designed to provide a connection between the first and second connecting regions. As the connecting piece is designed while the first and second models are placed at said relative position, the connecting piece will connect and maintain the leading edge module relative to the wing box as provided by the relative position. Accordingly, the leading edge module will be located relative to the wing box as required by the construction of the aircraft wing.

[0036] There Figure 4b shows an isolated connecting piece 10, for illustrative purposes only and not covered by the invention. The Figure 4a shows a digital model of the same connecting piece located between the digital model of the wing box and the digital module of the leading edge to provide a connection so as to establish the relative position 120 between the first and second connection regions.

[0037] In a fifth step, the connecting part is manufactured. For example, the connecting part can be manufactured by a mechanical machining process or by a 3D printing process.

[0038] In the example shown in the Figure 4a and 4b not covered by the invention, the connecting piece 10 comprises a plate 150. Said plate comprises at least two fixing openings 160, provided to establish a connection with the first and the second connection region and thus establish the connection between the wing box and the leading edge module. The first and the second connection region may comprise eyelets 170, as shown in the figure 1 , 2 , 3 And 4a The fixing openings 160 of the connecting plate are thus designed to establish a connection with the eyelets of the first and second region, for example by a screw or a rivet.

[0039] The step of designing the connecting piece comprises locating the openings on the connecting plate to be able to fix the plate between the eyelets 170 such that the first and second reference regions are located at said relative position 120. To achieve this result, the first and second digital models of the first and second representative parts of the wing box and the leading edge module are positioned so as to establish the relative position 120 between the first and second reference regions, as shown in the Figure 4a . Then, the digital model of the plate 150 is positioned between the eyelets of the first and second connection regions. The fastening openings 160 are positioned on the plate so as to coincide with the eyelets. Then, the plate comprising the fastening openings is manufactured, as shown in the Figure 4b .

[0040] The fabricated plate is then mounted between the wing box eyelets and the leading edge module eyelets, for example by passing screws through the respective openings. As a result of the manufacturing method described above, the first and second reference regions will be held at the chosen relative position 120 once the plate is mounted between the eyelets of the two connection regions. The leading edge module is thus mounted to the wing box as intended by the construction of the aircraft wing.

[0041] Advantageously, the first and second digital models may be acquired before the leading edge module arrives at the aircraft wing manufacturing line. For example, the aircraft wing including the wing box but without the leading edge module may be located on a manufacturing line at the aircraft manufacturer. The first digital model of the wing box may be acquired at the manufacturer without impeding other work being done on the wing. The leading edge module may be located at a supplier and the second digital model may be established at said supplier. Then, the plate (150) may be designed and manufactured. Once the leading edge module and the plate are delivered to the manufacturer, the leading edge module may be mounted directly to the wing box without the requirement to perform drilling or adaptation operations.The connecting piece manufacturing process described above ensures that the leading edge module is fixed in the desired position relative to the wing box.

[0042] THE Figures 5a, 5b and 5c show a connecting piece according to the invention. The connecting piece may comprise an eccentric guide ring 210, as shown in the Figure 5b . There Figure 5c shows a section of the ring 210. The ring includes an outer diameter 230 and an inner diameter 250. A central axis of the inner diameter is displaced relative to a central axis of the outer diameter by an eccentricity 220 of the ring.

[0043] In this case, the first and second connection regions comprise a first opening 240 and a second opening 260, as shown in the Figure 5a, located on the wing box and the leading edge module. The step of designing the connecting piece to provide a connection between the first and second connection regions comprises adapting at least the eccentricity 220 of the ring. It is also possible to adapt the outer diameter and / or the inner diameter of the ring.

[0044] To design the ring, the first digital model and the second digital model of the wing box and the leading edge module are located at the relative position 120 as previously described. Then, a digital model of the ring is designed to make an outside of the ring 230 coincide with the first opening 240 and an inside 250 of the ring with the second opening 260. In other words, following this adaptation and holding the wing box and the leading edge module at said relative position 120, the outside of the ring can be inserted into the first opening. A screw or a rivet can, at the same time, pass through the inside of the ring and the second opening. As described above, the eccentricity 220 of the ring is adapted for this purpose. It is also possible to adapt the outside diameter 230 and / or the inside diameter 250 of the ring.It is understood that the first opening can be located on the wing box and the second opening on the leading edge module or vice versa. The ring is then manufactured from the digital model of the ring.

[0045] The leading edge module is then mounted to the wing box using the ring made from the digital model. As shown in the Figure 5a , the ring makes it possible to establish the connection between the openings of the first connection region and the openings of the second connection region. For example, a screw can be used to fix the connection. The adaptation of the ring as described above has the consequence that the leading edge module and the wing box which are at the origin of the first and second digital model are held at the relative position 120. Thus, the leading edge module is mounted to the wing box as intended for the manufacture of the aircraft wing.

[0046] THE Figures 6a, 6b and 6c show another connecting piece, for illustrative purposes only and not covered by the invention. The Figure 6b shows a 180 multi-level plate which is an alternative to the 150 plate shown in the Figure 4b . As with the previously described plate, fixing openings 160 present on the plate are located on the plate in order to fix the plate between the first and second connection regions. The position of the fixing openings is established as previously described for the plate 150 shown in the Figure 4b . Said multi-level plate 180 is provided to establish a connection between two surfaces 200 located on the first and second connection regions, as shown in the Figure 6a . The multi-level plate includes a relative distance 190 of the plate levels, shown in the Figure 6c, used to establish the link between the two surfaces 200 forming part of the wing box and the leading edge module.

[0047] According to the method presented, the first and second numerical models each comprise the set of a reference region and a connection region. To design the connection part, the reference regions are used to establish a relative position. Then, the connection part is adapted according to the connection region. For the connection part and the leading edge module, the reference region and the connection region are thus at a fixed or temporarily fixed relative position. In other words, the first reference region is at a fixed or temporarily fixed position relative to the first connection region. The second reference region is at a fixed or temporarily fixed position relative to the second connection region.

[0048] For example, the first reference region may comprise a first device attached or temporarily attached to the wing box 130. The second reference region may comprise a second device attached to the leading edge 140. figures 2 And 3 show an example of a device temporarily attached to the wing box 140 or a device temporarily attached to the leading edge module 140. In the cases shown in the figures 2 And 3 , a transport frame has been attached to the wing box and / or the leading edge module. Since the transport frame remains temporarily fixed, a temporarily fixed relative position is established between a reference region located on said frame and a connection region of the leading edge module or the wing box.

[0049] The first and second reference regions may also be part of the wing box and leading edge module.

[0050] For example, as shown by the figure 7 , the first reference region may comprise an upper row of spar fasteners 270. The first reference region may also comprise a lower row of spar fasteners 280. The second reference region may for example comprise the upper surface of the main rib 300.

[0051] Following manufacture of the connecting piece, it is used throughout the wing box and leading edge module. It is also possible to use several connecting pieces to attach the leading edge module to the wing box, each of the connecting pieces manufactured according to the method described above. Thus, it is possible to use several rings 210. Two or more connecting pieces are referred to as being "of the same" type if each of the connecting pieces is a ring. Several parts of the same type used to attach the same leading edge module and wing box are referred to as a "set of parts of the same type". The leading edge module and the wing box can thus be attached by one or more sets of parts of the same type.

[0052] Each individual connecting piece has been adapted to the particular dimensions and positions determined by the first and second connecting regions which will be linked by that particular connecting piece.

[0053] Consequently, the different parts forming part of a set of parts of the same type are all different from each other. In other words, a first and a second ring forming part of the same set will be different at least with respect to their eccentricity. At least one distance measured on the first part is different from the same distance measured on the second part, said distance being for example the eccentricity or a distance from a fixing opening to an edge of the plate.

[0054] In this way, in an assembly of a wing box and a leading edge module in which the leading edge module is fixed to the wing box by a first and a second connecting piece of the same type, both said connecting pieces being a ring, the first connecting piece is not exchangeable with the second connecting piece.

[0055] In other words, since each connecting piece is individually adapted to its position in the assembly between attack module and wing box, a first and a second connecting piece of the same type cannot be exchanged or changed places with each other.

[0056] Similarly, two connecting pieces of the same type used in a first wing intended to equip a first aircraft and a second wing intended to equip a second aircraft cannot be exchanged or change places with each other. More specifically, the first piece is located at one position in the first wing. The second piece is located at the same position in the second wing. Since the first and second aircraft are of the same type, the same position exists in the first and second wings. Accordingly, the first and second connecting pieces are of the same type, namely a ring.

[0057] In other words, in an assembly of a first wing intended to equip a first aircraft and a second wing intended to equip a second aircraft, the first and second aircraft being of the same type, the first connecting piece is not exchangeable with the second connecting piece. As already described, the first wing comprises a first leading edge module fixed to a first box of the first wing by a first connecting piece located at a position in the first wing and the second wing comprises a second leading edge module fixed to a second box of the second wing by a second connecting piece located at said position in the second wing.

[0058] In particular, the two pieces are not exchangeable because at least one distance measured on the first piece is different from the same distance measured on the second piece.

[0059] Said measured distance may be for example a ring eccentricity (220). In this case, the difference is greater than 0 mm and less than 1.2 mm. According to another example the measured distance is an opening position on a plate. In this case, the difference is greater than 0 mm and less than 0.7 mm. The measured distance may be a distance between a center of the opening and an edge of the plate.

[0060] It is understood that the aforementioned assembly, which comprises the first wing and the second wing, may in reality comprise an even greater number of wings responding to the same principle. Such an assembly is found, for example, on an aircraft wing manufacturing site.

[0061] Similarly, the invention can be implemented in the form of an assembly formed by a first aircraft comprising a first wing, and a second aircraft equipped with a second wing, the first and second aircraft being of the same type, the first wing comprising a first leading edge module fixed to a first box of the first wing by a first connecting piece located at a position in the first wing, the second wing comprising a second leading edge module fixed to a second box of the second wing by a second connecting piece located at said position in the second wing, the two said connecting pieces each being a ring, the two said connecting pieces being manufactured according to the method described previously, the first connecting piece not being exchangeable with the second connecting piece.

[0062] Such a set is located, for example, on an aircraft assembly / fitting site.

Claims

1. Method for manufacturing a connecting part (10) between a wing box (20) and a leading edge module (30), the method comprising the steps: - performing a three-dimensional scan of a first representative part of the wing box (40) to obtain a first computer model (50), - performing a three-dimensional scan of a second representative part of the leading edge module (60) in order to obtain a second computer model (70), the first part comprising a first reference region (80) and a first connecting region (90), the second part comprising a second reference region (100) and a second connecting region (110), - defining a relative position (120) of the first reference region with respect to the second reference region, - from the first and second computer model, configuring the connecting part (10) to provide a connection between the first and the second connecting region such that the first and the second reference region are located in said relative position, - manufacturing the connecting part, - the connecting part comprising an eccentric guide ring (210) and - the step of configuring the connecting part to provide a connection between the first and the second connecting region comprises adjusting at least one eccentricity (220) of the ring to coincide an exterior of the ring (230) with a first aperture (240) and an interior (250) of the ring with a second aperture (260), the first and second aperture being located in the connecting region.

2. Method according to claim 1 in which the combination of the first reference region, the second reference region and said relative position is configured to uniquely determine a relative position between the wing box and the leading edge module.

3. Method according to claim 1 or 2 in which the first reference region comprises a first device fixed to the wing box (130) and / or the second reference region comprises a second device fixed to the leading edge (140).

4. Method according to at least one of the preceding claims in which the first reference region comprises a top row of spar fasteners (270) and / or a bottom row of spar fasteners (280) and / or the second reference region comprises a top surface of the main rib (300).

5. Method according to at least one of the preceding claims in which the three-dimensional scanning is performed by a 3D scanner or a stereovision device.

6. Method according to at least one of the preceding claims in which the connecting part is manufactured by a mechanical machining process or by a 3D printing process.

7. Assembly formed by a first wing intended to equip a first aircraft and a second wing intended to equip a second aircraft, the first and the second aircraft being of the same type, the first wing comprising a first leading edge module attached to a first box of the first wing by a first connecting part located in a position in the first wing, the second wing comprising a second leading edge module attached to a second box of the second wing by a second connecting part located in said position in the second wing, the two said connecting parts each being a ring, the two said connecting parts being manufactured according to any one of the preceding claims, the first connecting part not being interchangeable with the second connecting part.

8. Assembly according to claim 7 in which at least a distance measured on the first part is different from the same distance measured on the second part, preferably the measured distance being a ring eccentricity (220) and the difference being greater than 0 mm and less than 1.2 mm or the measured distance being an aperture position on a plate and the difference being greater than 0 mm and less than 0.7 mm.

9. Assembly formed by a first aircraft comprising a first wing, and a second aircraft fitted with a second wing, the first and the second aircraft being of the same type, the first wing comprising a first leading edge module attached to a first box of the first wing by a first connecting part located in a position in the first wing, the second wing comprising a second leading edge module attached to a second box of the second wing by a second connecting part located in said position in the second wing, the two said connecting parts each being a ring, the two said connecting parts being manufactured according to the method according to any one of claims 1 to 6, the first connecting part not being interchangeable with the second connecting part.