Rapid attachment for movable flap modules of aircraft wings

Abstract

The invention relates to a method for manufacturing a connecting portion (10) between a wing box (20) of an aircraft and a leading edge module (30). The method comprises the steps of three-dimensionally digitizing (40) a representative first portion of the wing box to obtain a first digital model (50) and three-dimensionally digitizing (60) a representative second portion of the leading edge module to obtain a second digital model (70). The first portion comprises a first reference area (80) and a first connecting area (90) and the second portion comprises a second reference area (100) and a second connecting area (110). A relative position (120) of the first reference area with respect to the second reference area is defined. Based on the first digital model and the second digital model, the connecting portion (10) is designed to provide a connection between the first connecting area and the second connecting area such that the first reference area and the second reference area are located at the relative position. The connecting portion is then manufactured. The invention also relates to an assembly comprising a first wing of a first aircraft and a second wing of a second aircraft.

Description

Technical Field

[0001] This invention relates to the field of a type of aircraft wing comprising a central wing body that is fixed and supports one or more movable leading-edge flaps, also known as "slats". Background Technology

[0002] Each of the two wings in an airfoil is typically equipped with movable, high-lift flaps mounted on the leading edge of the wing. The flaps deploy during landing and takeoff to increase lift at low or medium speeds. When cruising at high speeds, the movable flaps retract to limit drag on the aircraft's forward motion.

[0003] Currently, fitting a fixed leading edge and movable flaps to a wing involves numerous operations. Both the fixed leading edge and movable flaps consist of multiple parts, including, for example, ribs, skin, electrical systems, and guide rails, hinges, and pivot arms to enable the movable parts to perform the desired movements. During the assembly of the fixed leading edge and movable flaps, these different parts are individually joined to the wing through operations including drilling and riveting to form the fixed leading edge, and bolting and adjusting to install the movable flaps. During this time, other work on the wing cannot be performed, and the assembly line remains interrupted. Furthermore, the drilling operation tends to deposit metal shavings in the removable parts of the wing, which are then at risk of damage when they move.

[0004] Therefore, it would be advantageous to construct a leading edge module that includes a fixed leading edge, movable flaps and removable portions, which can be installed on the wing without the need for drilling operations on the assembly line. Summary of the Invention

[0005] Therefore, the object of the present invention is to provide a method for manufacturing a connection portion between a wing box and a leading edge module, the method comprising the steps described in one aspect of the present invention.

[0006] The first reference region, the second reference region, and the relative position can be configured to uniquely determine the relative position between the wing box and the leading edge module.

[0007] The first reference area may also include a first device fixed to the wing box, and / or

[0008] The second reference region includes a second device attached to the leading edge.

[0009] Advantageously, the connecting portion includes an eccentric guide ring, and the step of designing the connecting portion to provide a connection between a first connecting region and a second connecting region includes adjusting at least one eccentricity of the ring so that the outer side of the ring coincides with a first opening and the inner side of the ring coincides with a second opening, the first and second openings being located in the connecting regions.

[0010] Preferably, the first reference area includes the top row of spar fasteners and / or the bottom row of spar fasteners and / or the second reference area includes the upper surface of the main rib.

[0011] A 3D scan of a representative first part of the wing box and a 3D scan of a representative second part of the leading edge module can be performed using a 3D scanner or stereo vision device.

[0012] The connecting parts can be manufactured through machining or 3D printing.

[0013] The object of this invention is also a component according to another aspect of the invention.

[0014] In the component, at least one distance measured on the first connecting portion may differ from the distance measured on the second connecting portion, preferably by 3% or more.

[0015] The object of this invention is also a component consisting of a first aircraft including a first wing and a second aircraft equipped with a second wing.

[0016] The first and second aircraft are of the same type.

[0017] The first wing includes a first leading-edge module that is attached to a first wing box of the first wing via a first connecting portion located in the first wing.

[0018] The second wing includes a second leading-edge module that is attached to a second wing box of the second wing via a second connecting portion located at said position in the second wing.

[0019] Each of the two connecting portions is a loop.

[0020] The two connecting parts are manufactured according to the method described above.

[0021] The first connecting part and the second connecting part are not interchangeable. Attached Figure Description

[0022] The invention will be better understood from the following description and the accompanying drawings, in which:

[0023] - Figure 1 The image shows the fixed leading-edge module of the aircraft wing and the front portion of the wing box.

[0024] - Figure 2 The wing box, including the first connecting area, is shown.

[0025] - Figure 3 The leading edge module, including the second connection region, is shown.

[0026] - Figure 4a and Figure 4b A computer model and a board serving as a connecting part, not covered by this invention, are shown.

[0027] - Figure 5a , Figure 5b and Figure 5c The ring is shown as a connecting part.

[0028] - Figure 6a , Figure 6b and Figure 6c A multi-level plate serving as a connecting portion, not covered by this invention, is shown.

[0029] - Figure 7 The reference area is shown.

[0030] - Figure 8 The steps of a method for producing the connecting portion are shown. Detailed Implementation

[0031] Figure 1 The fixed leading edge module 30 of the aircraft wing and the front portion of the wing box 20 are shown.

[0032] The wing box is defined by a sparsity 500, a top skin 510, and a bottom skin 520. The wing box includes a first connection region 90 configured to mount a leading-edge module. Figure 1 In the example shown, the first connection area includes an eyelet 170.

[0033] The leading edge module 30 further includes a second connection region 110, which is configured to allow the leading edge module to be secured to the wing box. In the example shown, there are one or more eyelets.

[0034] Figure 8 A method for producing a connection portion between a wing box 20 and a leading edge module 30 is shown, providing said portion to secure the leading edge module to the wing box. Reference will be made below. Figures 2 to 7 The method will be explained.

[0035] In the first step 410, a three-dimensional scan 40 is performed on a representative first part of the wing box to obtain a first computer model 50.

[0036] Figure 2 A wing box 20 including a first connection region 90 is shown. A scanning device 290 is also shown. The scanning device 290 may be, for example, a 3D scanner or a stereo vision device. The scanning device is configured to perform a 3D scan of a representative first portion of the wing box. The representative portion may be, for example, the interior of the wing box. In this case, the scanning device is oriented to, for example, obtain a computer model of the interior of the wing box. The representative first portion includes a first connection region 90 and a first reference region 80. Therefore, the first computer model obtained from the scan includes the first connection region and the first reference region.

[0037] The first reference region is the visible portion of the computer model, which has a fixed or temporarily fixed position relative to the first connected region. For example, as Figure 2 As indicated, the first reference area 80 may be the top edge and / or bottom edge of the wing box. In this case, the position is fixed. The first reference area may also be a line or area located on the transport frame attached to the wing box. In this case, the position is temporarily fixed while the wing box remains connected to the transport frame.

[0038] In the second step, a three-dimensional scan 60 is performed on a representative second part of the leading edge module to obtain a second computer model 70.

[0039] Figure 3 A leading edge module 30 including a second connection region 110 is shown. In this case, the scanning device 290 is oriented and configured to perform a three-dimensional scan of a representative second portion of the leading edge module. In a manner similar to that described above, the representative second portion includes the second connection region 110 and a second reference region 100. A second computer model includes, and thus shows, the second connection region and the second reference region.

[0040] exist Figure 3 In the illustrated case, the second reference region is the interior of the leading edge module, including the top and / or bottom edges of the leading edge, and / or the surface of the central rib. As described above, 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 the transport frame 140 of the leading edge module.

[0041] In the third step 430, the relative position 120 of the first reference region with respect to the second reference region is defined.

[0042] Figure 4aA first computer model 50 of the wing box 20 and a second computer model 70 of the leading edge module 30 are shown. Since the scanned models have been obtained from the manufactured parts using scanning device 290, the models illustrate any potential manufacturing hazards. In other words, the relative dimensions of the two manufactured parts (the leading edge module and the specific wing box that has been scanned) are represented by the corresponding scanned models. The first computer model also includes a first reference region 80 and a first connection region 90 located on the wing box. The second computer model 70 includes a second reference region 100 and a second connection region 110.

[0043] The relative position 120 of the first reference region with respect to the second reference region can be, for example, a distance. The relative position 120 can also be a vector defined in three-dimensional space. For example, the vector can be defined in a reference frame fixed to the wing box or fixed to the leading edge module. Multiple first reference regions and / or multiple second reference regions can also be provided, and / or multiple associated relative positions can be defined. For example, as... Figure 4a As shown, two first reference regions and two second reference regions have been identified. In this case, two relative positions 120 are defined.

[0044] The first and second reference regions, along with the relative positions, are configured to obtain the relative positions of the leading edge module and the wing box, as intended for use in the construction of an aircraft wing.

[0045] Preferably, the combination of the first reference area, the second reference area, and the relative position uniquely determines the relative position between the wing box and the leading edge module.

[0046] As seen from the wing box or the leading edge module, the other part to be fitted has six degrees of freedom. In a Cartesian frame of reference fixed to one of the two parts (the leading edge module or the wing box), the other part has three translational degrees of freedom in the x, y, and z directions. The other part also has three rotational degrees of freedom about the x, y, and z axes.

[0047] Preferably, the combination of the first reference region, the second reference region, and the relative positions is thus configured to determine the six degrees of freedom (three translational degrees and three rotational degrees) of the leading edge module relative to the wing box, or to determine the six degrees of freedom (three translational degrees and three rotational degrees) of the wing box relative to the leading edge module.

[0048] In the fourth step 440, the connecting part 10 is constructed from the first computer model and the second computer model, which are positioned in the relative positions defined in the third step as described above.

[0049] The connecting portion is configured to provide a connection between the first connecting area and the second connecting area. When this connecting portion is constructed while the first and second models are positioned in their relative positions, the connecting portion will connect and hold the leading edge module relative to the wing box as provided by the relative positions. Therefore, the leading edge module will be positioned relative to the wing box according to the structural requirements of the aircraft wing.

[0050] Figure 4b A separate connection portion 10 is shown only by illustration and is not covered by this invention. Figure 4a A computer model showing the same connection portion between the computer model of the wing box and the computer model of the leading edge is shown to provide a connection between the first connection area and the second connection area to establish relative position 120.

[0051] In the fifth step, the connecting parts are fabricated. For example, the connecting parts can be fabricated through machining or 3D printing.

[0052] exist Figure 4a and Figure 4b In the illustrated example not covered by the present invention, the connecting portion 10 includes a plate 150. The plate includes at least two fixing openings 160 configured to connect with a first connecting region and a second connecting region, thereby establishing a connection between the wing box and the leading edge module. The first and second connecting regions may include eyelets 170, such as… Figure 1 , Figure 2 , Figure 3 and Figure 4a As shown in the diagram, the fixing opening 160 in the connecting plate is configured to connect, for example, to the eyelets in the first and second regions via screws or rivets.

[0053] The steps of constructing the connecting portion include positioning openings on the connecting plate such that the plate can be fastened between the holes 170, such that the first reference region and the second reference region are located in the relative position 120. To achieve this, a first computer model of a representative first portion of the wing box and a second computer model of a representative second portion of the leading edge module are positioned to establish the relative position 120 between the first and second reference regions, as follows: Figure 4a As shown in the diagram. Then, the computer model of board 150 is positioned between the holes in the first connection region and the holes in the second connection region. A fixing opening 160 is positioned on the board to coincide with the holes. Then, a board including the fixing opening is manufactured, as shown in the diagram. Figure 4b As shown in the figure.

[0054] Then, for example, by passing screws through the corresponding openings, the manufactured plate is installed between the eyelets of the wing box and the eyelets of the leading edge module. Due to the manufacturing method described above, once the plate is installed between the eyelets of the two connecting areas, the first reference area and the second reference area will be maintained in the selected relative position 120. The leading edge module is thus mounted on the wing box according to the configuration of the aircraft wing.

[0055] Advantageously, the first and second computer models can be obtained before the leading-edge module arrives at the aircraft wing production line. For example, an aircraft wing including a wing box but without the leading-edge module can be on the aircraft manufacturer's production line. The first computer model of the wing box can be obtained from the manufacturer without preventing further work on the wing. The leading-edge module can be located at the supplier, and the second computer model can be created by said supplier. Plate 150 can then be designed and manufactured. Once the leading-edge module and plate have been delivered to the manufacturer, the leading-edge module can be directly mounted onto the wing box without any drilling or fitting operations. The above-described method of manufacturing the connecting portion ensures that the leading-edge module is fixed in the desired position relative to the wing box.

[0056] Figure 5a , Figure 5b and Figure 5c A connection portion according to the present invention is shown. The connection portion may include, for example... Figure 5b The eccentric guide ring 210 shown is illustrated. Figure 5c A cross-section of ring 210 is shown. The ring has an outer diameter of 230 and an inner diameter of 250. The central axis of the inner diameter is shifted relative to the central axis of the outer diameter by an eccentricity of 220.

[0057] In this case, the first connection region and the second connection region include a first opening 240 and a second opening 260, such as Figure 5a As shown, the first opening 240 is located on the wing box and the second opening 260 is located on the leading edge module. The step of constructing the connection portion to provide a connection between the first and second connection areas includes at least the fact that the eccentricity 220 of the adjusting ring is adjusted. The outer diameter and / or inner diameter of the ring can also be adjusted.

[0058] To design the ring, a first computer model of the wing box and a second computer model of the leading edge module are positioned in the relative position 120 as described above. The computer model of the ring is then configured such that the outer edge 230 of the ring coincides with the first opening 240, and the inner edge 250 of the ring coincides with the second opening 260. In other words, after this adjustment and while holding the wing box and leading edge module in the relative position 120, the outer edge of the ring can be inserted into the first opening. Simultaneously, screws or rivets can pass through the inner edge of the ring and the second opening. For this purpose, the eccentricity 220 of the ring is adjusted as described above. The outer diameter 230 and / or the inner diameter 250 of the ring can also be adjusted. Of course, the first opening can be located on the wing box and the second opening can be located on the leading edge module, or vice versa. The ring is then produced according to the computer model of the ring.

[0059] Then, the leading-edge module is mounted on the wing box using a ring produced by a computer model. For example... Figure 5a As shown, the ring is used to establish a connection between the opening in the first connection region and the opening in the second connection region. For example, a screw can be used to secure this connection. The fitting of the ring as described above means that the leading-edge module and the wing box, which are the origins of the first and second computer models, are held in relative position 120. Thus, the leading-edge module is fitted to the wing box, as intended for use in the manufacture of an aircraft wing.

[0060] Figure 6a , Figure 6b and Figure 6c Another connection portion is shown for illustrative purposes only and is not covered by the present invention. Figure 6b Multilevel board 180 is shown. Multilevel board 180 is Figure 4b An alternative to the plate 150 shown is provided. Similar to the plate described above, a fixing opening 160 is located on the plate to secure the plate between the first connecting region and the second connecting region. As described above... Figure 4b The plate 150 shown defines the location of the fixing opening. The multi-level plate 180 is configured to establish a connection between two surfaces 200 located in the first and second connection regions, as shown below. Figure 6a As shown, a multi-level board has [missing information] between each level of the board. Figure 6c The relative distance 190 shown is used to establish a connection between two surfaces 200 that form part of the wing box and leading edge module.

[0061] According to the described method, the first computer model and the second computer model each include a reference region and a connection region. To design the connection portion, the reference region is used to establish a relative position. The connection portion is then adjusted according to the connection region. For the connection portion and the leading edge module, the reference region and the connection region are thus in a fixed or temporarily fixed relative position. In other words, the first reference region is in a fixed or temporarily fixed position relative to the first connection region. The second reference region is in a fixed or temporarily fixed position relative to the second connection region.

[0062] For example, the first reference area may include a first device 130 that is fixed or temporarily fixed to the wing box. The second reference area may include a second device 140 that is attached to the leading edge. Figure 2 and Figure 3 Examples of devices 140 for temporary attachment to the wing box or for temporary attachment to the leading edge module are shown. Figure 2 and Figure 3 In the scenario shown, the transport frame has been secured to the wing box and / or leading edge module. While the transport frame remains temporarily secured, a temporary fixed relative position is established between a reference area on the frame and the connection area of ​​the leading edge module or wing box.

[0063] The first reference area can also form part of the wing box and the second reference area can also form part of the leading edge module.

[0064] For example, such as Figure 7 As shown, the first reference region may include the top row of spar fasteners 270. The first reference region may also include the bottom row of spar fasteners 280. The second reference region may, for example, include the top surface of the main rib 300.

[0065] Once the connecting portion has been manufactured, it is used in the wing box and leading edge module assembly. Multiple connecting portions can also be used to secure the leading edge module to the wing box, each of which is manufactured according to the method described above. Therefore, multiple rings 210 can be used. If each connecting portion is a ring, then two or more connecting portions are referred to as being of the "same" type. Multiple portions of the same type used to secure the same leading edge module and wing box are referred to as a "set of portions of the same type." The leading edge module and wing box can therefore be secured using a set or more sets of portions of the same type.

[0066] Each individual connecting part has been adjusted to a specific size and position as defined by a first connecting area and a second connecting area, which will be connected by that specific connecting part.

[0067] Therefore, the different parts—parts forming a group of parts of the same type—are all different from each other. In other words, the first ring and the second ring—parts forming the same group—will differ at least in terms of their eccentricity. At least one distance measured on the first connecting portion will differ from the distance measured on the second connecting portion, such distance being, for example, eccentricity or the distance between the fixed opening and the edge of the plate.

[0068] In this way, in the following wing box and leading edge module assembly, the first connecting portion and the second connecting portion are not interchangeable: in this wing box and leading edge module assembly, the leading edge module is fixed to the wing box by the same type of first connecting portion and second connecting portion, the two connecting portions being loops.

[0069] In other words, since each connecting part is individually adjusted to its position within the assembly between the guide module and the wing box, first and second connecting parts of the same type cannot be interchanged or have their positions changed.

[0070] Similarly, two connecting parts of the same type used in the first wing intended to mount the first aircraft and the second wing intended to mount the second aircraft cannot be interchanged or have their positions changed. More specifically, the first connecting part is located in the first wing. The second connecting part is located in the second wing. Since the first and second aircraft are of the same type, they occupy the same positions in both wings. Therefore, the first and second connecting parts are of the same type, i.e., rings.

[0071] In other words, in the components of the first wing intended to equip the first aircraft and the second wing intended to equip the second aircraft, the first and second aircraft are of the same type, and the first and second connecting portions are not interchangeable. As already described, the first wing includes a first leading-edge module secured to a first wing box of the first wing via a first connecting portion located in a position within the first wing, and the second wing includes a second leading-edge module secured to a second wing box of the second wing via a second connecting portion located in the same position within the second wing.

[0072] In particular, these two parts are not interchangeable, because at least one distance measured on the first connecting part is different from the distance measured on the second connecting part.

[0073] The measured distance can be, for example, a ring eccentricity of 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 the location of an opening on the plate. In this case, the difference is greater than 0 mm and less than 0.7 mm. The measured distance can be the distance between the center of the opening and the edge of the plate.

[0074] It should be noted that the aforementioned components, including the first wing and the second wing, can actually comprise even more wings based on the same principle. For example, such components can be found at manufacturing sites for aircraft wings.

[0075] Similarly, the present invention may take the form of a component consisting of a first aircraft including a first wing and a second aircraft equipped with a second wing.

[0076] The first and second aircraft are of the same type.

[0077] The first wing includes a first leading-edge module that is attached to a first wing box of the first wing via a first connecting portion located in the first wing.

[0078] The second wing includes a second leading-edge module that is attached to a second wing box of the second wing via a second connecting portion located at said position in the second wing.

[0079] Each of the two connecting portions is a loop.

[0080] The two connecting parts are manufactured according to the method described above.

[0081] The first connecting part and the second connecting part are not interchangeable.

[0082] For example, such components can be found at the aircraft assembly / construction site.

Claims

1. A method for manufacturing a connection portion (10) between a wing box (20) and a leading edge module (30), the method comprising the steps of: - Perform a three-dimensional scan on a representative first portion of the wing box to obtain a first computer model (50). - Perform a three-dimensional scan on a representative second portion of the leading edge module to obtain a second computer model (70). The representative first part includes a first reference region (80) and a first connection region (90), and the representative second part includes a second reference region (100) and a second connection region (110). - Define the relative position of the first reference region with respect to the second reference region (120). - Based on the first computer model and the second computer model, the connection portion (10) is constructed to provide a connection between the first connection region and the second connection region, such that the first reference region and the second reference region are located in the relative positions. - Manufacture the connecting portion. - The connecting portion includes an eccentric guide ring (210), and - The step of constructing the connecting portion to provide a connection between the first connecting region and the second connecting region includes adjusting at least one eccentricity (220) of the eccentric guide ring such that the outer side (230) of the eccentric guide ring coincides with the first opening (240) and the inner side (250) of the eccentric guide ring coincides with the second opening (260), the first opening and the second opening being located in the connecting region.

2. The method according to claim 1, wherein, The combination of the first reference region, the second reference region, and the relative position uniquely determines the relative position between the wing box and the leading edge module.

3. The method according to claim 1 or 2, wherein, The first reference area includes a first device (130) fixed to the wing box, and / or The second reference region includes a second device (140) fixed to the leading edge.

4. The method according to claim 1 or 2, wherein, The first reference area includes the top row of spar fasteners (270) and / or the bottom row of spar fasteners (280), and / or The second reference region includes the top surface of the main rib (300).

5. The method according to claim 1 or 2, wherein, The three-dimensional scan of the representative first portion of the wing box and the three-dimensional scan of the representative second portion of the leading edge module are performed using a 3D scanner or stereoscopic vision device.

6. The method according to claim 1 or 2, wherein, The connecting parts are manufactured through machining or 3D printing.

7. An assembly comprising a first wing intended to be mounted on a first aircraft and a second wing intended to be mounted on a second aircraft. The first and second aircraft are of the same type. The first wing includes a first leading edge module, which is attached to a first wing box of the first wing via a first connecting portion located in the first wing. The second wing includes a second leading-edge module, which is attached to a second wing box of the second wing via a second connecting portion located at the aforementioned position in the second wing. Each of the two connecting portions is a loop. The two connecting portions are manufactured according to any one of claims 1 to 6. The first connecting portion and the second connecting portion are not interchangeable.

8. The component according to claim 7, wherein, At least one distance measured on the first connecting portion is different from the distance measured on the second connecting portion.

9. The component according to claim 8, wherein, The measured distance is the circumferential eccentricity (220) and the difference is greater than 0 mm and less than 1.2 mm, or The measured distance is the location of the opening on the plate, and the difference is greater than 0 mm and less than 0.7 mm.

10. An assembly comprising a first aircraft including a first wing and a second aircraft equipped with a second wing, The first and second aircraft are of the same type. The first wing includes a first leading edge module, which is attached to a first wing box of the first wing via a first connecting portion located in the first wing. The second wing includes a second leading-edge module, which is attached to a second wing box of the second wing via a second connecting portion located at the aforementioned position in the second wing. Each of the two connecting portions is a loop. The two connecting portions are manufactured according to the method described in any one of claims 1 to 6. The first connecting portion and the second connecting portion are not interchangeable.

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