Connection assembly, slat assembly, and aircraft comprising a slat assembly

Abstract

The invention relates to a C-shaped connection assembly for transferring loads between a first wing element and a second wing element in a load plane. The connection assembly comprises a first L-shaped load carrier and a second L-shaped load carrier. Each load carrier comprises an engagement region and two leg portions which extend parallel to the load plane and away from the engagement region towards a respective end region. One leg portion of the first load carrier extends parallel to one leg portion of the second load carrier. These leg portions are connected to each other. Two coupling portions for connecting the connection assembly to the second wing element are formed in the respective engagement regions of the load carriers. Two further coupling portions for connecting the connection assembly to the first wing element are formed in the respective free end regions of the load carriers and in the engagement region of the second load carrier. Furthermore, the invention also relates to a slat assembly for a main wing of an aircraft and to an aircraft comprising a slat assembly.

Description

Technical Field

[0001] This application relates to a connection assembly for transmitting loads in a load plane between a first wing element and a second wing element. Furthermore, this application relates to a slat assembly for an aircraft main wing and an aircraft including the slat assembly. Background Technology

[0002] To selectively alter the degree of lift provided by an aircraft wing, the wing typically incorporates aerodynamic surfaces movably coupled to the main wing. These aerodynamic surfaces can move between a retracted position and at least one deployed position. In the retracted position, the aerodynamic surface is disposed within or directly on the main wing. In the at least one deployed position, the aerodynamic surface extends from the main wing. A slat is a movable aerodynamic surface disposed at and capable of extending from the leading edge of the main wing.

[0003] Slats are typically mounted to the main wing via multiple elongated slat tracks. Each slat track is movable relative to the main wing between a retracted position and an extended position, where the retracted position corresponds to the slat's folded-down position and the extended position corresponds to the slat's deployed position. The movement of the slat track between the retracted and extended positions is achieved by a drive mechanism. For example, such a drive mechanism may include a drive shaft rotatably driven by a rotary actuator, and this drive shaft is coupled to each slat track via a corresponding transmission or gearbox that converts the rotational motion of the drive shaft into synchronous translational motion of the slat track along its longitudinal extension.

[0004] The connection between the slat track and the slat is typically achieved via a coupling comprising multiple spherical bearings, allowing for a degree of movement of the slat relative to the slat track. At least one of the couplings is configured as a so-called master coupling, which prevents lateral displacement between the slat and the corresponding slat track at the coupling's location. Some of the other couplings may be configured as so-called slave couplings, which allow such relative lateral displacement. In general, the coupling configuration allows for the compensation of minor changes in the slat's position and geometry relative to the slat track, thus maintaining at least a degree of disconnection between the deformation of the slat and the deformation of the master track.

[0005] For example, when the slat tracks connected to a single slat move asynchronously, i.e., when the slat tracks move at different speeds, a relative change in the position of the slat relative to the slat track may occur, resulting in slat skew. This relative change can be accommodated by a coupling constructed as described above. The relative change in the lateral position of the slat relative to the slat track may occur, for example, due to temperature-related variations in the dimensions along the slat's span. These variations can also be adjusted by the coupling described previously. However, the arrangement of spherical bearings used in the coupling, along with multiple connecting elements, is generally relatively complex, expensive, and space-consuming.

[0006] EP 3 326 909 A1 discloses an alternative interconnection between a slat and a slat track, the alternative interconnection being elastically deformable such that a first stiffness preventing deformation about a first axis is at least ten times a second stiffness preventing deformation about a second axis, and the first stiffness preventing deformation about the first axis is also at least ten times a third stiffness preventing deformation about a third axis, the second axis extending perpendicular to the first axis, and the third axis extending perpendicular to both the first and second axes. In a preferred embodiment, the interconnection comprises a plurality of plates having two opposing extended surfaces and arranged such that one extended surface is on top of the other extended surface, such that the extended surfaces of adjacent plates face each other, and the plates form a stack. The extended surfaces of the plates are perpendicular to the first axis. The slat is rigidly held on the main wing at the desired pitch angle, yet the interconnection is still able to adapt to forces and allow for violent movements that occur when the slat tilts.

[0007] Recent regulatory changes require interconnections not only to meet specified lateral and torsional load requirements, but also to provide robust and fail-safe connections that offer alternative load paths in the event of primary load path failure. Therefore, an object of the present invention is to provide an interconnection assembly between a first wing element and a second wing element. Another object is to provide a compact interconnection assembly that provides the required robustness and lateral flexibility. Summary of the Invention

[0008] This objective is achieved by the connecting assembly, slat assembly, and aircraft of the present invention. Preferred embodiments of the connecting assembly and slat assembly are also described herein.

[0009] In a first aspect, the problem to be solved by the present invention is addressed by a connecting assembly for transmitting load between a first wing element and a second wing element in a load plane. The connecting assembly is C-shaped and includes a first load-bearing device and a second load-bearing device. Each of the first and second load-bearing devices is L-shaped and includes a first leg, a second leg, and a joining region. The first leg extends parallel to the load plane and away from the joining region toward a first end region. The second leg extends parallel to the load plane and away from the joining region toward a second end region. The second legs of the first and second load-bearing devices extend parallel to each other. A first connecting portion is formed in the joining region of the first load-bearing device for connecting the connecting assembly to the second wing element. A second connecting portion is formed in the second end region of the first load-bearing device and the joining region of the second load-bearing device. A third connecting portion is formed in the first end region of the first load-bearing device for connecting the connecting assembly to the first wing element. A fourth connecting portion is formed in the first end region of the second load-bearing device for connecting the connecting assembly to the first wing element. The second leg of the second load-bearing device is connected to the second leg of the first load-bearing device.

[0010] In other words, a connecting assembly is provided for connecting a second wing element, such as a slat, to a first wing element, such as a slat track, and for transferring loads between the first and second wing elements. The connecting assembly is primarily intended to transfer loads acting in a load plane between the two wing elements. In the example of a connecting assembly connecting a slat to a slat track, the load plane may extend, for example, parallel to the plane in which the slat track moves as the slat moves between a retracted and deployed position.

[0011] The connecting assembly includes two load-bearing devices or elements configured to connect two wing elements and to transfer loads between the two wing elements. Both load-bearing devices are L-shaped, meaning they each include two legs extending away from the engagement area and forming an angle less than 180° but not necessarily precisely 90°. One leg of each load-bearing device is referred to as the first leg, and the other as the second leg. Each first leg extends away from the corresponding engagement area toward a first end area, and each second leg extends away from the corresponding engagement area toward a second end area. The first and second legs of the two load-bearing devices extend parallel to the load plane, but not necessarily in or directly adjacent to the load plane, or even in the same plane. Furthermore, the second legs of the load-bearing devices extend parallel to each other, but in opposite directions as will be described in more detail in the following paragraphs: the second leg of the first load-bearing device extends from the engagement area of ​​the first load-bearing device toward the engagement area of ​​the second load-bearing device, and the second leg of the second load-bearing device extends from the engagement area of ​​the second load-bearing device toward the engagement area of ​​the first load-bearing device. The first leg of the load-bearing device typically extends away from the corresponding joint area along the same, but not necessarily parallel, direction. In other words, when the first and second load-bearing devices are projected onto the load plane, the first leg of the load-bearing device is located on the same side of the axis connecting the joint areas of the load-bearing devices. Therefore, the shape of the connecting assembly formed by the first and second load-bearing devices can be described as C-shaped.

[0012] The first and second load-bearing devices can be arranged directly adjacent to each other or even as meshing elements. However, the first and second load-bearing devices can also be arranged spaced apart from each other in a direction perpendicular to the load plane, i.e., in the wingspan direction of the slats or main wing.

[0013] The connecting assembly includes four connecting portions configured to connect or mount the connecting assembly to a wing element: a first connecting portion and a second connecting portion are configured to connect the connecting assembly to a second wing element, and a third and fourth connecting portion are configured to connect the connecting assembly to a first wing element. The connecting portions are formed in one or both of the carrier device. The connecting portions may be formed in the carrier device, for example, by providing recesses or holes for receiving bolts or, more generally, connectors for mounting the connecting assembly to the respective wing element.

[0014] The first connecting portion is located in the engagement region of the first carrier, specifically at a position where the first and second legs of the first carrier extend away from each other. This first connecting portion may, but not necessarily, also be formed in the second end region of the second carrier. When a connector for connecting an assembly to one of the wing elements is connected to or extends through both respective carriers, a connecting portion is formed in both carriers. The second connecting portion is formed in both the engagement region of the second carrier and the second end region of the first carrier. Therefore, at the second connecting portion, both the first and second carriers are connected to the second wing element. The third and fourth connecting portions are each formed in the first end regions of the first and second carriers, respectively.

[0015] Therefore, the connecting assembly is designed such that it can be connected to each of the first and second wing elements at two mounting points. At the first wing element, each corresponding mounting point is connected to only one of the load-bearing devices. At the second wing element, at least one of the two mounting points, and preferably both mounting points, is connected to each of the load-bearing devices. At least the first load-bearing device is also adapted to connect the two mounting points on the second wing element, thereby fixing the position of the second wing element relative to the first wing element in the load plane.

[0016] In the attachment, the second leg of the first load-bearing device and the second leg of the second load-bearing device are connected to each other, so as to provide a second load path between the first wing element and the second wing element in the event of failure of the first load path.

[0017] In addition to providing two load paths, the connecting assembly according to the invention provides a robust connection between the first and second wing elements in the load plane. Specifically, high loads can be transmitted in the direction of the first arm of the L-shaped load-bearing device. In other words, the connecting assembly provides high bending stiffness to prevent rotation about an axis of motion that extends in the load plane and is generally parallel to the extension direction of the first arm of the L-shaped load-bearing device. For example, if the connecting assembly is used to connect a slat track, which is a first wing element, to a slat forming a second wing element, the connecting assembly can be used to ensure that the slats are in the same deployed position in the chord direction of the wing.

[0018] Furthermore, since the second leg of the first load-bearing device rigidly connects to the two mounting points at the second wing element, the connecting assembly is not so rigid with respect to rotation about a torsional axis extending perpendicular to the load plane. Therefore, under normal operating conditions, the connecting assembly can, for example, prevent the slat from twisting about an axis extending perpendicular to the load plane. On the other hand, under exceptionally high loads, the connecting assembly is not so rigid with respect to rotation about this axis and can achieve some differential rotation within the slat without failure.

[0019] Finally, the connecting assembly advantageously does not achieve high bending stiffness about an axis extending perpendicular to the torsional and / or motion axis. In the previously discussed slat example, the connecting assembly will not be very rigid to relative changes in the slat's position relative to the slat track in the spanwise direction. Therefore, the connecting assembly can compensate for variations in the spanwise extension of the slat, such as changes in the slat length due to temperature.

[0020] In a preferred embodiment, the second leg of the second bearing device is connected to the second leg of the first bearing device, such that the first bearing device and the second bearing device can rotate relative to each other about a predetermined first angle about an adjustment axis that extends perpendicular to the load plane and through the second connecting portion.

[0021] In other words, in a preferred embodiment, the shape of the C-shape is not fixed, but the opening angle of the C-shape can be changed. This allows, for example, the use of an eccentric bolt for connecting the first support device to the first wing element at the fourth connection portion. By rotating the eccentric bolt, the position of the second wing element relative to the first wing element can be adjusted. This makes the installation of the connection assembly easier. In the previously described example, the eccentric bolt can be used to adjust the position of the slat relative to the main wing on which the slat track is mounted. Exemplary embodiments of the connection assembly that allow for changing the opening angle are described as part of the following exemplary embodiments.

[0022] It is further preferred that the connecting assembly includes a first connector for connecting the connecting assembly to the second wing element at a first connecting portion and for connecting the second leg of the second load-bearing device to the engagement region of the first load-bearing device. The first connecting portion in the engagement region of the first load-bearing device is configured to receive the first connector in such a way that movement of the first load-bearing device relative to the first connector in a plane extending parallel to the load plane is prevented by the engagement of the first load-bearing device with the first connector. Furthermore, the first connecting portion is also formed in the second end region of the second load-bearing device. The first connecting portion in the second end region of the second load-bearing device is configured to limit relative rotation between the first and second load-bearing devices about an adjustment axis to a predetermined first angle by providing a first end stop and a second end stop, the first and second end stops being used for engagement of the first connector with the second load-bearing device.

[0023] In this preferred embodiment, a first connecting portion is also formed in the second load-bearing device. A connector, such as a bolt, is provided for connecting the connecting assembly to the second wing element. The first connecting portion in the first load-bearing device closely corresponds to the first connector or any bushing configured to mount the first connector in the first connecting portion. Since the position of the second wing element is also fixed relative to the first load-bearing device at the second connecting portion, the overall position of the second wing element relative to the first load-bearing element is well defined in a plane extending parallel to the load plane.

[0024] The position of the second wing element relative to the second load-bearing device is defined only at the second connecting portion in a plane extending parallel to the load plane. However, a connection between the second legs of the load-bearing device is provided by means of a first connector. Furthermore, the second wing element can rotate relative to the second load-bearing element about an adjustment axis. This rotation is limited by a first predetermined angle by means of an end stop provided at the first connecting portion in the second load-bearing element. This end stop can be defined, for example, by the shape of the first connecting portion in the second load-bearing device. Preferred shapes are described below as exemplary embodiments.

[0025] It should be noted that, since the first load-bearing device can rotate relative to the second load-bearing device, the second load path is not immediately available if, for example, the second leg of the first load-bearing device fails. The second load-bearing device may initially rotate relative to the second wing element until it reaches one of the end stops of the first connector engagement end stop. It should also be noted that, in this case, the stiffness of the connecting assembly with respect to rotation about an axis extending perpendicular to the load plane decreases with respect to the available clearance between the second load-bearing device and the first connector.

[0026] Preferably, the first connecting portion is configured as an elongated hole extending in a circle around the adjustment axis in the second end region of the second bearing device.

[0027] Alternatively, the shape of the first connecting portion in the second end region of the second bearing device when projected onto the load plane corresponds to the shape of the first connecting portion in the joint region of the first bearing device when projected onto the load plane, and the area of ​​the first connecting portion in the second end region of the second bearing device when projected onto the load plane exceeds the area of ​​the first connecting portion in the joint region of the first bearing device when projected onto the load plane.

[0028] In other words, the first connecting portion has a corresponding shape in the first and second supporting devices, but with different dimensions. For example, the first connecting portion may be cylindrical and have a narrower inner diameter in the first supporting device than in the second supporting device.

[0029] In a preferred embodiment, the first connector for connecting the connecting assembly to the second wing element at the first coupling portion is supported by a first bushing at least in the first carrier. Alternatively or additionally, the second connector for connecting the connecting assembly to the second wing element at the second coupling portion and connecting the first carrier to the second carrier is supported by a second bushing in both the first and second carriers. Further alternatively or additionally, the third connector for connecting the connecting assembly to the first wing element at the third coupling portion is supported by a third bushing in the first carrier. And even further additionally or alternatively, the fourth connector for connecting the connecting assembly to the first wing element at the fourth coupling portion is supported by a fourth bushing in the second carrier.

[0030] Preferably, a bushing is provided to reduce the load on the connector, and the bushing can also be used to compensate for manufacturing tolerances.

[0031] In another preferred embodiment, a fifth connecting portion for connecting the first bearing device to the second bearing device is formed in the second leg of the first bearing device and located between the engagement region and the second end region of the first bearing device. The fifth connecting portion is also formed in the second leg of the second bearing device and located between the engagement region and the second end region of the second bearing device. The connecting assembly further includes a fifth connector extending through the fifth connecting portion for transmitting a load acting parallel to the load plane between the second legs of the first and second bearing devices. In a preferred embodiment, the fifth connector is preferably supported by a fifth bushing in both the first and second bearing devices.

[0032] This preferred embodiment includes a fifth connecting portion and a corresponding fifth connector. The fifth connecting portion is configured to connect the first and second load-bearing devices and provide an additional load path between the second legs of the load-bearing devices. The fifth connecting portion can also be used to define the opening angle of the C-shape formed by the connecting assembly. Additionally, the fifth connecting portion improves the reliability of the C-shaped connecting assembly due to the additional load-bearing connection between the first and second load-bearing devices.

[0033] However, in a preferred embodiment, the opening angle of the C-shape is also variable when the fifth connecting portion is provided. Therefore, it is preferable that the fifth connecting portion in the second leg of the second bearing device is configured as an elongated hole extending in a circle about the adjustment axis. Alternatively, the shape of the fifth connecting portion in the second leg of the second bearing device when projected onto the load plane corresponds to the shape of the fifth connecting portion in the second leg of the first bearing device when projected onto the load plane, and the area of ​​the fifth connecting portion in the second leg of the second bearing device when projected onto the load plane exceeds the area of ​​the fifth connecting portion in the second leg of the first bearing device when projected onto the load plane.

[0034] Therefore, when the opening angle of the C-shape formed by the connecting components can be changed, the fifth connecting portion can be shaped in a similar manner to the first connecting portion. It should be noted that the fifth connecting portion can be used as an addition to or replacement for the first connecting portion, which is also formed in the second bearing device.

[0035] In a preferred embodiment, the first bearing device is formed of a plurality of first plates, and the second bearing device is formed of a plurality of second plates. Each of the plurality of first plates and each of the plurality of second plates has two opposing extending surfaces. Each extending surface extends parallel to the load plane. A first connecting portion, a second connecting portion, and a third connecting portion are at least partially formed in each of the plurality of first plates. A first connecting portion, a second connecting portion, and a fourth connecting portion are at least partially formed in each of the plurality of second plates. The plurality of first plates and the plurality of second plates are arranged in an alternating sequence, one on top of the other, such that each extending surface of a first plate directly adjacent to the extending surface of another plate is directly adjacent to the extending surface of a second plate, and each extending surface of a second plate directly adjacent to the extending surface of another plate is directly adjacent to the extending surface of a first plate.

[0036] In an exemplary embodiment, the first and second support devices are not solid elements, but are each formed of multiple plates. These plates are stacked one on top of the other, forming an interlocking structure. The use of stacked interlocking plates is particularly preferred because it significantly reduces the stiffness of the connecting assembly to bending about the axis of motion and has the advantages discussed above. The use of stacked plates advantageously makes it easier to control the stiffness of the connecting assembly by varying the number and thickness of the plates.

[0037] In a preferred embodiment, a first spacer is disposed between adjacent first plates of the first support device in the first end region of the first support device. Preferably, a third connecting portion is partially formed in the first spacer. Alternatively or additionally, a second spacer is disposed between adjacent second plates of the second support device in the first end region of the second support device. Preferably, a fourth connecting portion is partially formed in the second spacer.

[0038] The spacer plate is used to stabilize the first and second load-bearing devices at their respective first end regions. Without the spacer plate, a gap would exist between the corresponding first and second plates because the plate of the other load-bearing device would not extend as far (the load-bearing device would only be L-shaped, not the C-shaped of the entire connecting assembly). The first and second spacer plates can also advantageously be used, for example, to change the rigidity of the C-shaped connecting assembly by altering the material or size of the spacer plates. The first and second spacer plates can be particularly used to adjust the bending and torsional characteristics of the connecting assembly.

[0039] In an exemplary preferred embodiment, the first connecting portion is formed by a first cylindrical recess in one of a plurality of first plates and a plurality of second plates, wherein at least one first cylindrical recess in the plurality of first plates has a smaller inner diameter than each first cylindrical recess formed in the plurality of second plates, and preferably each first cylindrical recess has a smaller inner diameter. More preferably, the first cylindrical recess forming the first connecting portion is adapted to receive a first connector in the form of a first mounting bolt for connecting the connecting assembly to a second wing element. This exemplary embodiment makes it possible to change the opening angle of the connecting assembly.

[0040] The first bushing is preferably disposed in the first cylindrical recess for supporting the first mounting bolt. It is particularly preferred to use bushings to install the mounting bolt in the connecting portion formed in the plurality of first plates and plurality of second plates, because this can compensate for manufacturing differences and also reduce the stress on the mounting bolt, which would otherwise be applied to the mounting bolt due to the stress exerted on the bolt by the plurality of different plates acting individually on the bolt.

[0041] Furthermore, in an exemplary preferred embodiment, the second connecting portion is formed by a second cylindrical recess in one of a plurality of first plates and a plurality of second plates. The second cylindrical recess is adapted to receive a second connector, in the form of a second mounting bolt, for connecting the connecting assembly to the second wing element. For example, preferably, a second bushing is disposed in the second cylindrical recess to support the second mounting bolt. Alternatively or additionally, a third connecting portion is formed in one of the plurality of first plates by a third cylindrical recess. The third cylindrical recess is adapted to receive a third connector, in the form of a third mounting bolt, for connecting the connecting assembly to the first wing element. In an exemplary preferred embodiment, a third bushing is disposed in the third cylindrical recess to support the third mounting bolt. Alternatively or additionally, a fourth connecting portion is formed in one of the plurality of second plates by a fourth cylindrical recess. The fourth cylindrical recess is adapted to receive a fourth connector, in the form of a fourth mounting bolt, for connecting the connecting assembly to the first wing element. Preferably, a fourth bushing is disposed in the fourth cylindrical recess to support the fourth mounting bolt.

[0042] The use of a cylindrical recess is particularly preferred because it allows the connecting assembly to be attached or mounted to the wing element using bolts. Bolts require less space and are less expensive than previously used spherical bearings. However, it should be noted that this embodiment can also be used with spherical bearings if needed.

[0043] In another preferred embodiment, a clamping element is provided that extends around the second leg of the first bearing device and the second leg of the second bearing device and is located between the first connecting portion and the second connecting portion, and the clamping element holds the first bearing device and the second bearing device together such that a load acting parallel to the load plane can be transmitted between the second leg of the first bearing device and the second leg of the second bearing device via the clamping element.

[0044] The clamping element can be formed in a manner similar to that used to hold the plate-like members of a leaf spring together. If the clamping element is attached only after the connecting assembly is installed, the selection of the opening angle of the adjusting connecting assembly can be maintained.

[0045] On the other hand, the problem addressed by the present invention is solved by a slat assembly for the main wing of an aircraft. The slat assembly includes a slat and an elongated slat track, wherein the slat is connected to the slat track by means of a connecting assembly according to any of the foregoing embodiments, and wherein the slat track is used to movably connect the slat assembly to the main wing.

[0046] The advantages of the slat assembly correspond to the advantages of the connecting components used in the slat assembly.

[0047] More preferably, the first and second connecting portions are connected to the slat, and the third and fourth connecting portions are connected to the slat track. However, it should be noted that the first and second connecting portions may also be attached to the slat track, while the third and fourth connecting portions are connected to the slat.

[0048] Additionally, preferably, the slat includes a first limiting device and a second limiting device, wherein the first limiting device and the second limiting device are attached to the slat and configured to engage at least one of the second legs of the first support device and the second support device to limit the rotation of at least one of the first support device and the second support device relative to the slat about the adjustment axis at a predetermined second angle.

[0049] The limiting device provides additional means for ensuring the second load path and limiting the relative rotation of the first and second load-bearing devices relative to each other.

[0050] Finally, in another aspect, the problem to be solved by the present invention is addressed by an aircraft comprising a main wing and a slat assembly according to any of the foregoing embodiments, wherein the slats of the slat assembly are mounted to the main wing by means of slat tracks and connecting components.

[0051] The advantages of different implementations of the aircraft correspond to the advantages of the implementation of the slat assembly used in the aircraft. Attached Figure Description

[0052] In the following description, the invention will be further described in detail with reference to exemplary embodiments of the connecting components, slat assemblies, and aircraft shown in the accompanying drawings, in which:

[0053] Figure 1 A cross-sectional view of an exemplary embodiment of a slat assembly including a connecting component is shown;

[0054] Figure 2 It shows Figure 1 Side view of the connecting components;

[0055] Figure 3 It shows Figure 2 A partially exploded view of the connecting components;

[0056] Figure 4 It shows Figure 2 A further exploded view of the connecting components;

[0057] Figure 5 It shows Figure 2 An elevation view of the connecting components;

[0058] Figure 6A side view of a second exemplary embodiment of the connecting component is shown;

[0059] Figure 7 It shows Figure 6 An elevation view of the connecting components;

[0060] Figure 8 A side view of a third exemplary embodiment of the connecting component is shown;

[0061] Figure 9 It shows Figure 8 An elevation view of the connecting components;

[0062] Figure 10 A second exemplary embodiment of the slat assembly is shown;

[0063] Figure 11 An exemplary implementation of the aircraft is shown;

[0064] Figure 12 It shows Figure 2 An exploded diagram of the connecting components; and

[0065] Figure 13 An alternative implementation of the second support device is shown. Detailed Implementation

[0066] In the following text, reference will be made to Figures 1 to 5 and Figure 12 A first exemplary embodiment of the connecting component 1 used in the slat assembly 3 is described. Throughout the figures, the same reference numerals are used to denote the same elements. Not all features of the exemplary embodiment are depicted in all figures. In particular, the slat assembly 3 is only used in… Figure 1 The figure shows the connection component 1 in all the figures. Where features are particularly well depicted in a particular figure, reference will be made to that figure. Unless otherwise stated, it should be understood that the figures at least show those features of the exemplary embodiments specifically referred to in the description.

[0067] Figure 1 An exemplary embodiment of the connecting assembly 1 is shown, which serves as part of the slat assembly 3 for connecting a first wing element 5, in the form of a slat track 7, to a second wing element 9, in the form of a slat 11. The slat track 7 is installed only on... Figure 1 The main wing 13 is shown in the middle section. The slat track 7 is configured to allow the slat 11 to... Figure 1 The collapsed position shown moves between one or more expanded positions not shown in the figure.

[0068] The slat track 7 is also referred to as the slat track 7 because it is intended to define the position of the slat 11 relative to the main wing 13 only in the load plane 15, and is intended to allow displacement of the slat 11 relative to the main wing 13 and the slat track 7 in a spanwise direction perpendicular to the axis extending from the load plane 15. The load plane 15 corresponds to... Figure 1 The cutting plane of the cross-sectional view shown corresponds to or extends parallel to the following plane of motion: the slat track 7 moves in this plane of motion as the slat 11 moves between a retracted position and an extended position. A drive mechanism is provided on the main wing 13 for moving the slat track 7 relative to the main wing 13. However, the drive mechanism is not shown in the figures.

[0069] The connecting assembly 1 is C-shaped and includes a first L-shaped support device 17 and a second L-shaped support device 19. Each of the support devices 17 and 19 includes: first legs 21 and 23; second legs 25 and 27; and engagement regions 29 and 31. The second legs 27 and engagement region 31 of the second support device 19 are not... Figure 1 As shown in the diagram, but for example, it can be found in... Figure 5 As observed, the first legs 21 and 23 of the support devices 17 and 19 extend from their respective engagement regions 29 and 31 toward the first end regions 33 and 35; the second legs 25 and 27 extend from their respective engagement regions 29 and 31 toward the second end regions 37 and 39. The support devices are L-shaped because the respective first legs 21 and 23 and the second legs 25 and 27 form an angle of less than 180°, preferably about 90°.

[0070] If possible Figure 1 As observed, the connecting assembly 1 includes four connecting portions 41, 43, 45, and 47, at which the connecting assembly is connected to or mounted to the first wing element 5 and the second wing element 9. Specifically, connecting portions 41 and 43 are configured to mount the connecting assembly 1 to the second wing element 9, and the third connecting portion 45 and the fourth connecting portion 47 are configured to mount the connecting assembly 1 to the first wing element 5.

[0071] Connecting portions 41, 43, 45, and 47 are formed in different parts of the C-shaped connecting assembly. Not all connecting portions 41, 43, 45, and 47 are formed in the two supporting devices 17 and 19. Figure 1In the exemplary embodiment shown, a first connecting portion 41 is formed in the engagement region 29 of the first support device 17 and the second end region 39 of the second support device 19. A second connecting portion 43 is always formed in the second end region 37 of the first support device 17 and the engagement region 31 of the second support device 19. A third connecting portion 45 and a fourth connecting portion 47 are formed in the first end region 33 of the first support device 17 and the first end region 35 of the second support device 19, respectively.

[0072] Therefore, the slat track 7 is connected to each of the load-bearing devices 17 and 19 at only one connecting portion 45, 47. On the other hand, the slat 11 is connected to each of the first load-bearing device 17 and the second load-bearing device 19 at two connecting portions 41, 43. This ensures that once the connecting assembly 1 is installed, the position of the slat 11 relative to the slat track 7 is well defined in the load plane 15.

[0073] Additionally, the connecting assembly 1 provides high rigidity to prevent rotation between the slat track 7 and the slat 11 about a motion axis 49, which extends generally parallel to the first legs 21, 23 of the support devices 17, 19 and parallel to the load plane 15. Therefore, the connecting assembly 1 provides robust positioning of the slat 11 in the deployed position.

[0074] Furthermore, the connecting assembly 1 is robust to rotation about the wingspan axis 51 via two connections established between the slat 11 and the second leg 25 of the first support device 17. This advantageously prevents twisting of the slat 11 in the wingspan direction and ensures a well-defined position relative to the main wing 13.

[0075] The connecting assembly 1 provides only very limited stiffness to prevent rotation between the slat 11 and the slat track 7 about a third axis 53, which extends perpendicular to the motion axis 49 and the spanwise axis 51. This advantageously allows for changes in the position of the slat 11 and the slat track 7 in the relevant spanwise direction, compensating for lateral extension changes in the slat 7, such as due to temperature variations, without the need for expensive and heavy spherical bearings.

[0076] The connecting assembly 1 is also robust because it provides two distinct load paths between the slat 11 and the slat track 7 via two independent support devices 17 and 19. Even if one of the support devices 17 and 19 fails, the other support device will still be able to provide sufficiently accurate positioning of the slat 7 relative to the slat track 11.

[0077] As in Figure 3 As best observed, the opening angle of the C-shaped connecting component 1 can be... Figures 1 to 5Variations are shown in the exemplary embodiments illustrated. Specifically, it is possible to rotate the first support device 17 and the second support device 19 relative to each other about an adjustment axis 55. This adjustment axis 55 extends perpendicular to the load plane 15 and through the second connecting portion 43. Providing a variable opening angle allows for compensation of manufacturing tolerances and also allows for adjustment of the relative positions of the slat 11 and the main wing 13. For this purpose, the connecting assembly 1 can be connected to the slat track 7 at the third connecting portion 45 using an eccentric mounting bolt 57. By rotating the eccentric mounting bolt 57, the relative positions of the first support device 17 and the slat track 7 in a plane extending parallel to the load plane 15 can be varied. Figure 1 An adjustment mechanism 59 is shown, which is configured to fix the rotational position of the mounting bolt 57 relative to the slat track 7.

[0078] The relative movement between the first support device 17 and the second support device 19 is made possible by the different dimensions of the first connecting portion 41 in the first support device 17 and the second support device 19. For example... Figure 3 As best observed, the first connecting portion 41 is cylindrical in both the first support device 17 and the second support device 19. However, the first connecting portion 41 has a narrower inner diameter in the first support device 17 than in the second support device 19. Therefore, the second support device 19 can rotate about the adjustment axis 55 until the first connector 61 engages with the second support device 19, the first connector 61 extending through the first connecting portion 41, for example, through the first mounting bolt, and the second support device 19 defining a recess forming the first connecting portion 41. The first connector 61 only... Figure 1 As shown in the image.

[0079] Because the width of the first connecting portion 41 in the second support device 19 limits the angle at which the first support device 17 and the second support device 19 can rotate relative to each other, they can only rotate around a predetermined limited angle.

[0080] Figure 13 An alternative embodiment of the second support device 19 is shown. This noteworthy embodiment is capable of... Figures 1 to 5 It is used in the connection component 1 shown. Figure 13 The second support device 19 differs from the previously discussed second support device 19 in that the first connecting portion 41 is formed as an elongated hole 63 instead of a cylindrical hole. The elongated hole 63 follows an arc about the adjustment axis 55 and guides the first connector 61 within it as the first support device 17 and the second support device 19 rotate relative to each other about the adjustment axis 55. The lateral ends 64 and 65 of the elongated hole 63 form a first end stop 64 and a second end stop 65, thereby defining the angle at which the first support device 17 and the second support device 19 can rotate relative to each other.

[0081] Figure 13 The remaining features of the second support device 19 shown correspond to Figures 1 to 5 The features of the second load-bearing device 19 shown are therefore not discussed further here. It should be noted that, since relative rotation of the first load-bearing device 17 and the second load-bearing device 19 is possible, the second load path may not be immediately available in the event of failure of the first load-bearing device 17, because the second load-bearing device 19 will need to rotate relative to the second wing element 9 until the first connector 61 engages with the edge of the second load-bearing device 19, thereby defining an excessively large first connection portion in the second load-bearing device 19.

[0082] The first support device 17 and the second support device 19 of the connecting assembly 1 are not formed from individual components. Instead, the first support device 17 and the second support device 19 of the connecting assembly 1 are each composed of a plurality of first plates 67 and second plates 69, as shown below. Figure 12 The exploded view is best shown. The first plate 67 and the second plate 69 each include two extending surfaces that extend parallel to the load plane 15. From... Figure 12 It can also be learned that the first and second bearing devices are arranged in an alternating sequence, i.e., the first and second bearing devices mesh with each other. Therefore, each first plate 67 is arranged directly adjacent to at least one second plate 69, such that each extended surface of the first plates 67, 69—each extended surface of the first plates 67, 69 in direct contact with another extended surface of the first plate 67 or the second plate 69—is in direct contact with the extended surface of the second plate 69, and vice versa.

[0083] The connecting assembly 1 also includes a first spacer 71 and a second spacer 73, each arranged between adjacent first plates 67 and second plates 69, and within their respective first end regions 33 and 35. When the first support device 17 and the second support device 19 do not overlap, i.e., when the first support device 17 and the second support device 19 are not directly adjacent to each other, the spacers 71 and 73 fill the gap between the first plate 67 and the second plate 69. A third connecting portion 45 and a fourth connecting portion 47 are also formed in the first spacer 71 and the second spacer 73, as shown in... Figure 12 What was observed in the study.

[0084] exist Figure 12 In the figures, only a few first end regions 33, 35 and only a few third and fourth connecting portions are indicated by reference numerals, so that... Figure 12 Easy to understand. For the same reason, several other reference numerals have also been omitted from the figures.

[0085] The advantage of the first support device 17 and the second support device 19, arranged in the form of a stack of first plates 67 and second plates 69, is that the support devices have high torsional stiffness about the axis of movement 49, low torsional stiffness about the wingspan axis 51, and very low torsional stiffness about the third axis 53. As already discussed, the different torsional stiffnesses are advantageous for mounting the slat 11 to the slat track 7 because the different torsional stiffnesses allow for the elimination of the previously required expensive, heavy, and bulky spherical bearings. Furthermore, having two parallel first legs 21, 23 allows for the design of a compact connecting assembly 1 that requires only a small space between the slat 11 and the main wing 13. This is particularly advantageous from an aerodynamic point of view.

[0086] from Figure 12 As can be most clearly observed, the first connecting portion 41, the second connecting portion 43, the third connecting portion 45 and the fourth connecting portion 47 are formed as cylindrical recesses extending in the first plate 67 and the second plate 69, as well as the first spacer 71 and the second spacer 73.

[0087] at last, Figure 1 , Figure 2 , Figure 4 and Figure 5 The arrangement in ( Figure 1 , Figure 2 and Figure 5 ) or to be arranged in ( Figure 4 The corresponding first connecting portion 41, second connecting portion 43, third connecting portion 45, and fourth connecting portion 47 have first bushings 75, second bushings 77, third bushings 79, and fourth bushings 81. Bushings 75, 77, 79, and 81 are configured to mount the corresponding first connector or mounting bolt 61, second connector or mounting bolt 83, third connector or mounting bolt 57, and fourth connector or mounting bolt 85 into the corresponding connecting portions 41, 43, 45, and 47, respectively. Bushings 75, 77, 79, and 81 advantageously compensate for manufacturing tolerances and reduce localized stresses applied to the mounting bolts 61, 83, 57, and 85 through the multiple edges of the first plate 67 and second plate 69, and the first spacer 71 and second spacer 73. Mounting bolts 61, 83, 57, and 85 are only... Figure 1 As shown in the image.

[0088] Figure 6 and Figure 7 A second embodiment of the connection component 1 is shown. The following will only describe the second embodiment in conjunction with reference to... Figures 1 to 5 , Figure 12 and Figure 13 The components described are those that are implemented in different ways.

[0089] Figure 6 and Figure 7 The difference between the connecting component 1 and the first embodiment lies in the inclusion of a fifth connecting portion 87. This fifth connecting portion 87 is formed within the second leg 25 of the first support device 17 and the second leg 27 of the second support device 19, and is located between the first connecting portion 41 and the second connecting portion 43. A fifth connector 89 is arranged in the fifth connecting portion 87 and connects the first support device 17 and the second support device 19. Thus, a load path is provided between the first support device 17 and the second support device 19 to improve the robustness of the connecting component 1 in the event of failure of one of the support devices 17 or 19. For example, it can be... Figure 6 and Figure 7 As observed, the fifth connector 89 is supported by the fifth support member 91 or has connecting bolts arranged in the fifth support member 91. The fifth support member 91 has the same advantages as the aforementioned supports 75, 77, 79, and 81.

[0090] In order to keep the opening angle of the C-shaped connecting assembly 1 variable, the fifth connecting portion 87 can be designed in a similar manner to the first connecting portion 41, wherein the fifth connecting portion 87 is oversized in the second bearing device 19 to allow relative rotational movement of the first bearing device 17 and the second bearing device 19 about the adjustment axis 55, and an end stop is provided to limit the rotation to a predetermined angle.

[0091] A third exemplary embodiment of the connection component 1 is in Figure 8 and Figure 9 As shown in the figure. Only the third exemplary embodiment will be discussed. Figures 1 to 5 and Figure 12 The features that differ from those of the first exemplary embodiment shown will be described in more detail.

[0092] In a third exemplary embodiment, the clamping element 93, also referred to as the clamping device 93, extends around the second leg 25 of the first support device 17 and the second leg 27 of the second support device 19, and holds the support devices 17 and 19 together. Therefore, the clamping device 93 provides an auxiliary load path in the event of failure of either the first support device 17 or the second support device 19. If the clamping device 93 is installed after the connection assembly 1 is installed, the selection of the opening angle of the adjustable C-shaped connection assembly 1 can be maintained.

[0093] Figure 10 A second exemplary embodiment of the slat assembly 3 is shown. (Only applicable to...) Figure 10 The second exemplary embodiment and reference Figure 1 Those elements that differ from the corresponding elements of the first exemplary embodiment described herein will be described in more detail. Figure 10 Several figure labels have been omitted to make the figures easier to understand.

[0094] The second exemplary embodiment of the slat assembly 3 and Figure 1 The slat assembly 3 differs only in the presence of two limiting devices 95, 97, which are, for example, attached to a protrusion or shaft of the slat 11. When the first support device 17 and / or the second support device 19 rotates relative to the slat 11 about the adjustment axis 55, the corresponding second legs 25, 27 of the first support device 17 and / or the second support device 19 eventually engage with one of the first limiting devices 95 and the second limiting device 97. Thus, the limiting devices 95, 97 restrict the relative angular movement of the first support device 17 and the second support device 19 relative to the slat 11 to a predetermined angle. Therefore, by means of the first limiting devices 95 and the second limiting devices 97, an auxiliary load path is provided in the event of failure of one of the first support device 17 and the second support device 19.

[0095] at last, Figure 11 An exemplary embodiment of an aircraft 99 comprising two main wings 101, 103 is shown. Each of the main wings 101, 103 includes a plurality of slats 105, spoilers 107, flaps 109, and ailerons 111. In the exemplary embodiment, the slats 105 of the aircraft 99 are part of an exemplary embodiment of a slat assembly 3 used, and the slats 105 of the aircraft 99 are at least partially mounted to the main wings 101, 103 of the aircraft 99 using a slat assembly 3 of a connecting assembly according to any of the exemplary embodiments in the exemplary embodiment. The connecting assembly is not in Figure 11 As shown in the figure. For example, the spoiler 107 or flap 109 can also be mounted to the main wings 101, 103 using a connection assembly of one of the exemplary embodiments in the exemplary embodiments.

[0096] The advantages of the aircraft 99 correspond to the advantages of the slat assembly and connecting assembly used in the aircraft.

Claims

1. A connecting assembly (1) for transmitting loads in a load plane (15) between a first wing element (5, 7) and a second wing element (9, 11), wherein, The connecting assembly (1) is C-shaped and includes a first support device (17) and a second support device (19), wherein each of the first support device (17) and the second support device (19) is L-shaped and includes a first leg (21, 23), a second leg (25, 27), and a joint area (29, 31), wherein the first leg (21, 23) extends parallel to the load plane (15) and away from the joint area (29, 31) toward a first end area (33, 35), and wherein the second leg (25, 27) extends parallel to the load plane (15) and away from the joint area (29, 31) toward a second end area (37, 39), wherein the second leg (25) of the first support device (17) and the second leg (27) of the second support device (19) extend parallel to each other. In this system, a first connecting portion (41) is formed in the engagement area (29) of the first support device (17), which is used to connect the connecting assembly (1) to the second wing element (9, 11). A second connecting portion (43) is formed in the second end area (37) of the first support device (17) and the engagement area (31) of the second support device (19), which is used to connect the connecting assembly (1) to the second wing element (9, 11). A third connecting portion (45) is formed in the first end area (33) of the first support device (17), which is used to connect the connecting assembly (1) to the first wing element (5, 7). A fourth connecting portion (47) is formed in the first end area (35) of the second support device (19), which is used to connect the connecting assembly (1) to the first wing element (5, 7). The second leg (27) of the second support device (19) is connected to the second leg (25) of the first support device (17).

2. The connecting component (1) according to claim 1, wherein, The second leg (27) of the second bearing device (19) is connected to the second leg (25) of the first bearing device (17), such that the first bearing device (17) and the second bearing device (19) can rotate relative to each other and about an adjustment axis (55) extending perpendicularly to the load plane (15) and through the second connecting portion (43).

3. The connecting component (1) according to claim 2, wherein, The connecting assembly (1) includes a first connector (61) for connecting the connecting assembly (1) to the second wing element (9, 11) at the first connecting portion (41), and for connecting the second leg (27) of the second carrier (19) to the engagement area (29) of the first carrier (17). The first connecting portion (41) is configured in the engagement region (29) of the first carrier (17) to receive the first connector (61) in such a way that the engagement of the first carrier (17) with the first connector (61) prevents movement of the first carrier (17) relative to the first connector (61) in a plane extending parallel to the load plane (15). The first connecting portion (41) is also formed in the second end region (39) of the second support device (19). The first connecting portion (41) in the second end region (39) of the second support device (19) is configured to limit the relative rotation between the first support device (17) and the second support device (19) about the adjustment axis (55) to the predetermined first angle by providing a first end stop (64) and a second end stop (65) for the engagement of the first connector (61) and the second support device (19).

4. The connecting component (1) according to claim 3, wherein, The first connecting portion (41) is configured in the second end region (39) of the second bearing device (19) as an elongated hole (63) extending along a circle around the adjustment axis (55), or Wherein, the shape of the first connecting portion (41) in the second end region (39) of the second bearing device (19) when projected onto the load plane (15) corresponds to the shape of the first connecting portion (41) in the joint region (29) of the first bearing device (17) when projected onto the load plane (15), and wherein, the area of ​​the first connecting portion (41) in the second end region (39) of the second bearing device (19) when projected onto the load plane (15) exceeds the area of ​​the first connecting portion (41) in the joint region (29) of the first bearing device (17) when projected onto the load plane (15).

5. The connecting component (1) according to any one of claims 3 and 4, wherein, The first connector (61) for connecting the connecting assembly (1) to the second wing element (9, 11) at the first connecting portion (41) is supported by a first bushing (75) at least in the first carrier (17), and / or Wherein, the second connector (83) for connecting the connecting assembly (1) to the second wing element (9, 11) at the second connecting portion (43) and connecting the first carrier device (17) to the second carrier device (19) is supported by a second bushing (77) in the first carrier device (17) and the second carrier device (19), and / or The third connector (57) for connecting the connecting assembly (1) to the first wing element (5, 7) at the third connecting portion (45) is supported by a third bushing (79) in the first bearing device (17), and / or The fourth connector (85) for connecting the connecting assembly (1) to the first wing element (5, 7) at the fourth connecting portion (47) is supported by the fourth bushing (81) in the second bearing device (19).

6. The connecting component (1) according to any one of claims 2 to 4, wherein, A fifth connecting portion (87) for connecting the first support device (17) to the second support device (19) is formed in the second leg (25) of the first support device (17) and located between the engagement region (29) and the second end region (37) of the first support device (17), and wherein the fifth connecting portion (87) is also formed in the second leg (27) of the second support device (19) and located between the engagement region (31) and the second end region (39) of the second support device (19). The connecting assembly (1) further includes a fifth connector (89) that extends through the fifth connecting portion (87) for transmitting a load acting parallel to the load plane (15) between the second leg (25) of the first bearing device (17) and the second leg (27) of the second bearing device (19). The fifth connector (89) is supported by a fifth bushing (91) in the first support device (17) and the second support device (19).

7. The connecting component (1) according to claim 6, wherein, The fifth connecting portion (87) is constructed in the second leg (27) of the second bearing device (19) as an elongated hole extending along a circle around the adjusting axis (55), or Wherein, the shape of the fifth connecting portion (87) in the second leg (27) of the second bearing device (19) when projected onto the load plane (15) corresponds to the shape of the fifth connecting portion (87) in the second leg (25) of the first bearing device (17) when projected onto the load plane (15), and wherein, the area of ​​the fifth connecting portion (87) in the second leg (27) of the second bearing device (19) when projected onto the load plane (15) exceeds the area of ​​the fifth connecting portion (87) in the second leg (25) of the first bearing device (17) when projected onto the load plane (15).

8. The connecting component (1) according to any one of claims 1 to 4, wherein, The first support device (17) is formed of a plurality of first plates (67), and the second support device (19) is formed of a plurality of second plates (69), wherein each of the plurality of first plates (67) and each of the plurality of second plates (69) has two opposing extending surfaces, wherein each extending surface extends parallel to the load plane (15). The first connecting portion (41), the second connecting portion (43) and the third connecting portion (45) are at least partially formed in each of the plurality of first plates (67), and the first connecting portion (41), the second connecting portion (43) and the fourth connecting portion (47) are at least partially formed in each of the plurality of second plates (69). The plurality of first plates (67) and the plurality of second plates (69) are arranged in an alternating order in a stacked manner, such that each of the extended surfaces of the first plate (67) directly adjacent to the other plate is arranged to be directly adjacent to the extended surface of the second plate (69) among the plurality of second plates (69), and each of the extended surfaces of the second plate (69) directly adjacent to the other plate is arranged to be directly adjacent to the extended surface of the first plate (67) among the plurality of first plates (67).

9. The connection component (1) according to claim 8, wherein, In the first end region (33) of the first support device (17), a first spacer plate (73) is arranged between adjacent first plates (67) of the first support device (17), wherein the third connecting portion (45) is partially formed in the first spacer plate (73), and / or In the first end region (35) of the second support device (19), a second spacer (71) is arranged between adjacent second plates (69) of the second support device (19), wherein the fourth connecting portion (47) is partially formed in the second spacer (71).

10. The connection component (1) according to claim 8, wherein, The first connecting portion (41) is formed by a first cylindrical recess in one of the plurality of first plates (67) and the plurality of second plates (69), wherein the inner diameter of at least one first cylindrical recess in the plurality of first plates (67) is smaller than the inner diameter of each first cylindrical recess in the plurality of second plates (69).

11. The connection component (1) according to claim 10, wherein, The inner diameter of each first cylindrical recess formed in the plurality of first plates (67) is smaller than the inner diameter of each first cylindrical recess formed in the plurality of second plates (69).

12. The connecting component (1) according to any one of claims 1 to 4, wherein, A clamping element (93) is provided, which extends around the second leg (25) of the first support device (17) and the second leg (27) of the second support device (19) and is located between the first connecting portion (41) and the second connecting portion (43), and the clamping element (93) holds the first support device (17) and the second support device (19) together, so that a load acting parallel to the load plane (15) can be transmitted between the second leg (25) of the first support device (17) and the second leg (27) of the second support device (19) via the clamping element (93).

13. A slat assembly (3) for the main wing (13, 101, 103) of an aircraft (99), the slat assembly (3) comprising slats (11, 105) and an elongated slat track (7), wherein, The slats (11, 105) are connected to the slat track (7) by means of a connecting assembly (1) according to any one of the preceding claims, wherein the slat track (7) is configured to movably connect the slat assembly (3) to the main wing (13, 101, 103).

14. The slat assembly (3) according to claim 13, wherein, The first connecting portion (41) and the second connecting portion (43) are connected to the slats (11, 105), and the third connecting portion (45) and the fourth connecting portion (47) are connected to the slat track (7).

15. The slat assembly (3) according to claim 13 or 14, wherein, The slats (11, 105) include a first limiting device (95) and a second limiting device (97), wherein the first limiting device (95) and the second limiting device (97) are attached to the slats (11) and configured to engage with at least one of the second leg (25) of the first support device (17) and the second leg (27) of the second support device (19) to limit the rotation of at least one of the first support device (17) and the second support device (19) relative to the slats (11) about an adjustment axis (55) that extends perpendicular to the load plane (15) and through the second connecting portion (43) to a predetermined second angle.

16. An aircraft (99) comprising a main wing (101, 103) and a slat assembly (3) according to claim 13, 14 or 15, wherein, The slats (11, 105) of the slat assembly (3) are mounted to the main wing (101, 103) by means of the slat track (7) and the connecting assembly (1).

Images