Forewing wing filler device for an aircraft wing, associated wing, wing surface, aircraft and method for reconfiguring a wing surface

Abstract

This leading edge slat filler device (24) for a leading edge slat (18) of an aircraft (10) comprises a cover panel (46) extending along a span direction (Y) and comprising a proximal edge (50) configured to be attached to a leading edge body (22) of the leading edge slat (18) and a distal edge (52) configured to be displaceable relative to the leading edge body (22), wherein the cover panel (46) comprises a plurality of guide passages, each guide passage being configured to interact with a guide element of the leading edge body (22) to guide the distal edge (52) along a displacement direction (S) relative to the leading edge body (22).

Description

[0001] The present disclosure relates to a leading-edge slat filler device of an aircraft. The present disclosure also relates to a leading-edge slat comprising such a leading-edge slat filler device. The present disclosure further relates to a wing comprising such a leading-edge slat and an aircraft comprising such a wing. The present disclosure also relates to a method for reconfiguring a wing as described above.

[0002] In the area of ​​leading-edge slats on aircraft, it is known that the leading-edge slat groove, i.e., the concave trailing edge of the slat, can be susceptible to turbulent airflow. The leading-edge slat groove is generally filled by the leading edge of a fixed wing section when the slat is in a retracted position. However, when the slat is extended, the leading-edge slat groove is exposed to ambient airflow. Such ambient airflow can penetrate the leading-edge slat groove, and due to its shape and position, this generally results in turbulent airflow at the groove. Therefore, such leading-edge slat grooves generally generate undesirable drag when the slat is extended, and also produce undesirable noise.

[0003] It was therefore suggested to use leading edge slat filler to fill the groove of leading edge slats, especially when leading edge slats are extended.

[0004] Known solutions are based, for example, on leading-edge slat filler devices that rely on a flexible panel which can be deformed to allow the leading-edge slat to retract relative to an aircraft wing, but which can also deform elastically so that the flexible panel fills the leading-edge slat filler when the slat is extended. In known solutions, the flexible panel is, for example, only supported at the trailing edge of one leading-edge slat body, and the opposite end of the flexible panel interacts freely with another leading-edge slat body.

[0005] However, such a solution is not entirely satisfactory. In fact, the loads exerted on such flexible panels can be considerable, and known leading-edge slat filler devices are not robust enough to guarantee satisfactory operational reliability.

[0006] One object of the present invention is therefore to provide a robust leading edge flap filler device that efficiently reduces air resistance and noise.

[0007] For this purpose, the invention relates to a leading edge slat filler device for a leading edge slat of an aircraft, wherein the leading edge slat filler device comprises a cover panel extending along a span direction and comprising a proximal edge configured to be attached to a leading edge body of the leading edge slat and a distal edge configured to be displaceable relative to the leading edge body, wherein the cover panel comprises a plurality of guide passages, each guide passage being configured to interact with a guide element of the leading edge body to guide the distal edge along a displacement direction relative to the leading edge body.

[0008] The use of a leading edge slat filler device comprising a cover panel with a plurality of guide passages, and in which each guide passage is configured to guide the distal edge of the cover panel along a displacement direction, is particularly advantageous because it allows the leading edge slat filler device to move properly to fill the leading edge slat when the leading edge slat is in an extended position, while ensuring that the displacement of the leading edge slat filler device is controlled and that the loads exerted on this device are limited.

[0009] According to further advantageous aspects of the invention, the leading edge flap filler device comprises one or more of the following features, individually or in all technically possible combinations: - the cover panel is flexible and configured to be deformable between the leading edge slat body and a fixed wing section of the aircraft when the leading edge slat body is displaced relative to the fixed wing section of the aircraft; - the guide passages are elongated along the direction of displacement, with the direction of displacement being essentially perpendicular to the span direction; - the multitude of guide passages is adjacent to the distal edge, with each guide passage being formed by an elongated hole or a notch; - the leading edge filler device further comprises at least one limiting element, wherein the limiting element is connected to the cover panel and configured to interact with the leading edge body to limit the displacement of the distal edge relative to the leading edge body along the direction of displacement; and - the limiting element comprises an elastic tongue, wherein a tip of the elastic tongue is configured to interact with the leading edge body to limit the displacement of the distal edge relative to the leading edge body.

[0010] The invention also relates to a leading edge slat comprising a leading edge slat filler device as shown above and a leading edge slat body, wherein the proximal edge of the cover panel of the leading edge slat filler device is attached to the leading edge slat body and the distal edge of the cover panel is displaceable relative to the leading edge slat body, wherein the leading edge slat body comprises a plurality of guide elements, each guide passage of the cover panel being configured to interact with one of the guide elements to guide the distal edge along the direction of displacement relative to the leading edge slat body.

[0011] According to further advantageous aspects of the invention, the leading edge slat comprises one or more of the following features, individually or in all technically possible combinations: - the leading edge slat body comprises an outer skin and an inner skin, the cover panel being configured to slide between the inner and outer skins so that the distal edge slides relative to the leading edge slat body; - at least one of the guide elements connects the inner and outer skin; - the leading edge body comprises at least one spacer, wherein the spacer is arranged between the inner skin and the outer skin to separate the inner skin from the outer skin; - the leading edge slat body comprises a plurality of spacers, each spacer being arranged around one of the guide elements, each guide element being configured to interact with one of the guide passages through the spacer to guide the distal edge along the direction of displacement relative to the leading edge slat body; and - the leading edge slat body further comprises at least one blocking element, wherein the blocking element is connected to the inner skin and is configured to interact with the leading edge slat filler device to block the displacement of the leading edge slat filler device along the displacement direction.

[0012] The invention also relates to a wing comprising a leading edge slat as shown above and a fixed wing section, wherein the leading edge slat is movable relative to the fixed wing section between an extended position and a retracted position, wherein the distal edge of the cover panel of the leading edge slat filler device is configured to slide relative to the leading edge body when the leading edge slat is moved between its extended and retracted positions.

[0013] The invention further relates to an aircraft comprising a wing as shown above.

[0014] The invention also relates to a method for reconfiguring a wing as shown above, wherein the method comprises the following steps: - Moving the leading edge slat relative to the fixed wing section between its extended and retracted positions, and - Sliding of the distal edge of the cover panel of the leading edge slat filler device relative to the leading edge body, wherein the sliding of the distal edge is guided along a displacement direction relative to the leading edge body, the displacement direction being defined by the guide passages of the cover panel.

[0015] The invention will be better understood by reading the following description, which is given only as an example and with reference to the accompanying drawings, in which: - Fig. 1 a schematic view of an aircraft comprising a wing with a leading edge slat according to the invention; - Fig. 2 a schematic sectional view, taken along a sectioning plane P, which is in Fig. 1 shown wing in which the leading edge slat filler device is visible and in which the leading edge slat is in an extended configuration relative to a fixed wing section of the wing; - Fig. 3 is a detailed schematic sectional view of a leading edge slat comprising a leading edge slat filler device according to an example of the invention; - Fig. 4 a schematic perspective view of the in Fig. The leading edge flap filler device shown in section 3 is; - Fig. 5 is a detailed schematic sectional view of a leading edge slat comprising a leading edge slat filler device according to a further example of the invention; and - Fig. 6 a schematic perspective view of the in Fig. The leading edge flap filler device shown in section 5 is shown.

[0016] With reference to Fig. 1 comprises an aircraft 10, a fuselage 12 and two wings 14.

[0017] Aircraft 10, for example, is an airplane, and for example, a commercial airliner.

[0018] Each wing 14 comprises a fixed wing section 16 and at least one leading edge slat 18.

[0019] As in Fig. As shown in Figure 1, the fixed wing section 16 includes a leading edge 20. The leading edge 20 of the fixed wing section 16, for example, faces the leading edge slat 18.

[0020] The leading edge slat 18 is positioned upstream of an ambient airflow F of the fixed wing section 16 when the aircraft 10 is in flight. It is therefore understood that the leading edge slat 18 is, for example, part of a leading-edge high-lift system.

[0021] As from Fig. As can be seen in Figure 1, the leading edge slat 18 is elongated along a span direction Y, where the span direction Y along which the leading edge slat 18 is elongated corresponds, for example, to a span direction of the wing 14.

[0022] The leading edge slat 18 is movable relative to the fixed wing section 16 between an extended and a retracted position. When the leading edge slat 18 is in its extended position, it is, for example, further away from the fixed wing section 16 than when it is in its retracted position.

[0023] The leading edge slat 18, for example, is movable in rotation and / or translation relative to the fixed wing section between its extended and retracted positions. In one example, the leading edge slat is attached to a curved rail (not shown), the curved rail being movable relative to the fixed wing section 16 to move the leading edge slat between its extended and retracted positions.

[0024] For example, the leading edge slat 18 is controlled so that it is in its extended position when high lift is required, such as during takeoff and / or landing of the aircraft 10, and is controlled so that it is in its retracted position when low drag is required, such as during cruise flight of the aircraft 10.

[0025] It is understood that there can be a multitude of extended positions for the leading edge slat 18, whereby the leading edge slat 18 is then movable between its extended positions and its retracted position.

[0026] As in Fig. As shown in Figure 2, the leading edge slat 18 comprises a leading edge slat body 22 and a leading edge slat filler device 24. It is understood that Fig. 2 represents a profile of the leading edge slat 22 along a section plane P, such that the leading edge body 22 and the leading edge slat filler device 24 are elongated, for example, along the span direction Y, wherein the span direction Y is, for example, substantially perpendicular to the section plane.

[0027] As from Fig. 2 and from the detailed descriptions of the Fig. 3 and Fig. As can be seen in Figure 5, the leading edge body 22 comprises an outer skin 26 and an inner skin 28.

[0028] The leading edge slat body 22 also includes a plurality of guide elements 30. For example, the leading edge slat body 22 further includes at least one spacer 32 and at least one locking element 34.

[0029] The outer skin 26 forms, for example, a leading edge of the leading edge flap 18. The outer skin 26 is then, for example, arranged upstream of the inner skin 28 relative to the ambient flow F.

[0030] The outer skin 26 is formed, for example, by a curved panel and / or includes, for example, a first edge 36 and a second edge 38, wherein both the first 36 and the second edge 38 extend substantially along the span direction Y.

[0031] As from Fig. As can be seen in Figure 2, the outer skin 26 defines, for example, a cavity 40.

[0032] The inner skin 28 extends, for example, at least into the cavity 40 defined by the outer skin 26.

[0033] The inner skin 28 is formed, for example, by a curved panel and / or includes, for example, a first edge 42 and a second edge 44, wherein both the first 42 and the second edge 444 extend substantially along the span direction Y.

[0034] The inner skin 28, for example, together with the outer skin 26, defines an internal volume V of the leading edge body 22.

[0035] Furthermore, as can be seen from Fig. As can be seen in Figure 2, the inner skin 28 is curved, for example, such that it defines a leading-edge groove 41 on one side of the inner skin 28 that is opposite the inner volume V. In particular, and in other words, the leading-edge groove 41 is a concave region defined by the inner skin 28 on the side of the inner skin 28 that is opposite the outer skin 26.

[0036] As from Fig. As can be seen in Figure 2, the inner skin 28 is curved along a profile which includes a multitude of turning points, such that the curve defines, for example, the leading edge groove 41, but also so that the first 42 and the second 44 edge can be connected to the outer skin 26 in areas where the outer skin 26 and the inner skin 28 are essentially parallel, as will be shown later.

[0037] As will be shown later, the leading edge slat groove 41 is configured to accommodate at least part of the fixed wing section 16, at least when the leading edge slat 18 is in its retracted position.

[0038] As from Fig. As can be seen in Figure 2, the inner skin 28 extends, for example, through the cavity 40 and connects, for example, the first 36 and the second 38 edge of the outer skin 26.

[0039] The first edge 36 of the outer skin 26 is connected, for example, to the first edge 42 of the inner skin 28, and the second edge 38 of the outer skin 26 is connected, for example, to the second edge 44 of the inner skin 28, as shown by dashed lines in Fig. 2 shown. Here, for example, it is understood that the term edge is to be understood as sections of the membranes 26, 28 that border the ends of the membranes 26, 28.

[0040] For example, the first edge 36 of the outer skin 26 is in contact with the first edge 42 of the inner skin 28, wherein the first edges 36, 42 are, for example, screwed and / or welded together.

[0041] For example, the second edge 38 of the outer skin 26 and the second edge 44 of the inner skin 28 are connected by a connecting element (without reference numeral) and, as will be shown in more detail later, connected, for example, by the guide element 30.

[0042] As will be shown in more detail later, the guide element 30 is configured to work together with the leading edge slat filler device 24 to guide the leading edge slat filler device relative to the leading edge body 22.

[0043] Furthermore, and for example, as in the Fig. 3 and Fig. As shown in Figure 5, the guide element 30 connects the inner skin 28 and the outer skin 26.

[0044] For example, the guide element 30 is formed by a bolt that extends through the inner skin 28 and the outer skin 26. For example, and as shown in the Fig. 3 and Fig. As shown in Figure 5, the bolt is flush with an outer surface (without reference numeral) of the outer skin 26.

[0045] The spacer 32 is arranged between the inner skin 28 and the outer skin 26.

[0046] As from the Fig. 3 and Fig. As can be seen in Figure 5, the spacer 32 is configured, for example, to space the inner skin 28 away from the outer skin 26.

[0047] In particular, as for example in the Fig. 3 and Fig. As shown in Figure 5, the spacer has a height H such that the distance between the second edge 38 of the outer skin 26 and the second edge 44 of the inner skin 28 is essentially equal to the height H.

[0048] The height H of the spacer 32, i.e. the distance between the second edge 38 of the outer skin 26 and the second edge 44 of the inner skin 28, is, for example, between 3 mm and 30 mm.

[0049] For example, the leading edge slat body 22 comprises a plurality of spacers 32. In particular, as in the example of the Fig. 3 and Fig. As shown in Figure 5, each spacer 32 is arranged around one of the guide elements 30, for example.

[0050] As in Fig. As shown in Figure 2, the leading edge slat filler device 24 is arranged, for example, between the leading edge slat body 22 and the fixed wing section 16. As will be shown in more detail later, the leading edge slat filler device 24 is configured, for example, to interact with the fixed wing section 16, at least when the leading edge slat 18 is in its retracted position.

[0051] As in the Fig. 2, Fig. 3, Fig. 4, Fig. 5 to Fig. As shown in Figure 6, the leading edge flap filler device 24 comprises a cover panel 46. In some examples, the leading edge flap filler device 24 also comprises at least one limiting element 48.

[0052] The cover panel 46 extends along a span direction, where the span direction corresponds, for example, to the span direction Y of the leading edge slat.

[0053] In the remainder of the description, the span direction of the wing 14, the leading edge slat 18 and the cover panel 46 are generally referred to as the span direction Y.

[0054] The cover panel 46, for example, comprises a proximal edge 50 and a distal edge 52. Both the proximal edge 50 and the distal edge 52 extend, for example, essentially along the span direction Y.

[0055] For example, the distal edge 52 is further away from the fixed wing section 16 than the proximal edge 50. For example, as shown from Fig. As can be seen in Figure 2, the distal edge 52 is located in an intrados region (without reference numeral) of the wing 14 and the proximal edge 50 is located in an extrados region (without reference numeral) of the wing 14.

[0056] As from Fig. 2 and from the Fig. 4 and Fig. As can be seen in Figure 16, the cover panel 46 is formed by a curved panel. For example, the profile of the curve that defines the cover panel 46 is essentially sigmoidal in shape.

[0057] As from Fig. As can be seen in Figure 2, the cover panel 46, for example, defines a concave region 54 facing the leading edge groove 41. The cover panel 46, together with the inner skin 28, thus defines a closed groove region R. As shown in Figure 2, the cover panel 46, for example, defines a closed groove region R. Fig. As can be seen in Figure 2, the leading edge flap groove 41 is arranged in the closed groove region R when the leading edge flap is in an extended position.

[0058] The cover panel 46 is, for example, flexible. In particular, the cover panel 46 is configured, for example, to be deformable between the leading edge slat body 22 and the fixed wing section 16 when the leading edge slat body is displaced relative to the fixed wing section of the aircraft.

[0059] The shape of the cover panel 46 depends, for example, on the position of the leading edge slat 22 relative to the fixed wing section 16. For example, the shape of the cover panel 46 is different when the leading edge slat 18 is in its extended position and when the leading edge slat is in its retracted position.

[0060] In particular, as can be seen from Fig. As can be seen in Figure 2, the leading edge slat filler device 24 is configured, for example, to interact with the fixed wing section 16 in such a way that the leading edge slat filler device is deformed.

[0061] The shape of the closed hollow region R then depends, for example, on the position of the leading edge slat body 22 relative to the fixed wing section 16.

[0062] As shown above, the leading edge slat groove 41 is located within the closed groove region R when the leading edge slat is in an extended position. However, the fixed wing section 16 is configured, for example, to deform the cover panel 46 so that the fixed section 16 can be accommodated in the leading edge slat groove 41 when the leading edge slat 18 is in its retracted position. In other words, when the leading edge slat 18 is moved towards its retracted position, the fixed wing section 16 pushes the cover panel 46 towards the leading edge slat body 22, thereby reducing the size of the closed groove region R and allowing the fixed wing section 16 to occupy the leading edge slat groove 41.

[0063] The proximal edge 50 of the cover panel 46 is attached to the leading edge slat body 22. For example, the proximal edge 50 is screwed and / or welded to the leading edge slat body 22.

[0064] In particular, as in Fig. As shown in Figure 2, the cover panel 46 is, for example, attached to the inner skin 28 of the leading edge slat body 22. For example, the proximal edge 50 of the cover panel 46 is attached to the first edge 42 of the inner skin 28.

[0065] The cover panel 46 is configured to be movable relative to the leading edge slat body 22.

[0066] In particular, the distal edge 52 is configured to be displaceable relative to the leading edge body 22.

[0067] As from the Fig. 3, Fig. 4, Fig. 5 to Fig. As can be seen in Figure 6, the cover panel includes a large number of guide passages 56.

[0068] Each guide passage 56 is configured to interact with a guide element 30 of the leading edge slat body 22.

[0069] As will be shown in more detail later, each guide passage 56 is specifically configured to work in conjunction with a guide element 30 to guide the distal edge 52 of the cover panel 46 along a displacement direction S relative to the leading edge body 22.

[0070] As from the Fig. 3 and Fig. As can be seen in Figure 5, each guide element 30 is configured, for example, to interact with one of the guide passages 56 through one of the spacers 32 in order to guide the distal edge 52 along the displacement direction S relative to the leading edge slat body 22. In an example not shown, each guide element 30 is configured to interact directly with one of the guide passages 56 in order to guide the distal edge 52 along the displacement direction S relative to the leading edge slat body 22.

[0071] As from the Fig. 4 and Fig. As can be seen in Figure 6, the guide passages 56 are, for example, elongated along the displacement direction S. In particular, the guide passages 56 define the displacement direction S such that the guide passages 56 are aligned with the displacement direction S.

[0072] The displacement direction S, for example, runs essentially perpendicular to the span direction Y.

[0073] As in the Fig. 4 and Fig. As shown in Figure 6, the multitude of guide passages 56 are adjacent to the distal edge 52. Each guide passage 56 is formed, for example, by an elongated hole or a notch.

[0074] Especially in the example of Fig. 4 each guide passage 56 is formed by a slot.

[0075] In the example of Fig. 6, each guide passage 56 is formed by a notch.

[0076] In an example not shown, the guide passages 56 are formed by both elongated holes and notches.

[0077] The distal edge 52 is configured, for example, to slide relative to the leading edge slat 22 when the leading edge slat 18 moves between its extended and retracted positions relative to the fixed wing section 16. The fixed wing section 16 is configured, for example, to interact with the cover panel 46 such that the distal edge 52 is moved relative to the leading edge slat 22 and guided along the displacement direction S by the interaction between the guide elements 30 and the guide passages 56.

[0078] The cover panel 46 is configured, for example, to slide between the inner skin 28 and the outer skin 26, such that the distal edge 52 slides relative to the leading edge body 22. In particular, the cover panel 46 is configured to slide between the second edge 38 of the outer skin 26 and the second edge 44 of the inner skin 28.

[0079] The thickness of the cover panel 46, and for example the distal edge 52 of the cover panel 46, is, for example, between 75% and 99% of the distance between the second edge 38 of the outer skin 26 and the second edge 44 of the inner skin 28, i.e., for example, between 75% and 99% of the height H of the spacer.

[0080] As will be explained in more detail later, the sliding of the distal edge 52 relative to the leading edge body 22 is limited to a guide length L. For example, the guide length L is between 50 mm and 1000 mm.

[0081] In the example of the Fig. 3 and Fig. 4, in which each guide passage 56 is an elongated hole, the displacement of the cover panel 46 relative to the leading edge body is limited, for example, by the length of the elongated hole along the displacement direction S, which corresponds, for example, to the guide length L.

[0082] In some examples and as mentioned above, the leading edge slat filler device 24 includes at least one limiting element 48 and / or the leading edge slat body 22 includes at least one blocking element 34.

[0083] The displacement of the cover panel 46 relative to the leading edge slat body 22 is limited, for example, by the limiting element 48 and / or the blocking element 34.

[0084] Especially in the example that is in the Fig. 5 and Fig. As shown in Figure 6, in which the guide passages 56 are formed by notches, the leading edge flap filler device 24, for example, comprises at least one limiting element 48 and the leading edge flap body 22 comprises at least one locking element 34. In particular, in the example of Fig. 5 and Fig. 6 the leading edge flap filling device 24, for example, comprises a plurality of limiting elements 48 and the leading edge flap body 22 comprises a blocking element 34.

[0085] In this example and as shown Fig. As shown in Figure 5, the guide length L is limited, for example, by one end of the notch (not referenced) and the limiting element 48.

[0086] As from Fig. As can be seen in Figure 5, the blocking element 34 is connected to the inner skin 28 and configured to interact with the leading edge slat filler 24 to block the displacement of the leading edge slat filler 24 along the displacement direction S. For example, the blocking element 34 is configured to interact with the limiting element(s) of the leading edge slat filler 24.

[0087] In the example of Fig. 5 The blocking element 34 is formed by an L-shaped profile that is attached to the inner skin 28. In particular, in the example of Fig. 5 the locking element is attached to the leading edge body with at least one of the guide elements 30, wherein the guide element 30 in this example, and as shown above, is formed by a bolt.

[0088] As from the Fig. 5 and Fig. As can be seen in Figure 6, the limiting element 48 is connected to the cover panel 46 and configured to interact with the leading edge slat body 22 to limit the displacement of the distal edge 52 relative to the leading edge slat body 22 along the displacement direction S. For example, the limiting element 48 is configured to interact with the locking element(s) 34 of the leading edge slat body 22.

[0089] In the example that is in Fig. As shown in Figure 5, each boundary element 48 includes an elastic tongue 58.

[0090] As from Fig. As can be seen in Figure 5, each elastic tongue 58 protrudes, for example, from the cover panel 46 towards the inner skin 28 and / or towards the blocking element 34.

[0091] As in Fig. As shown in Figure 5, a tip 60 of the elastic tongue 58 is configured, for example, to interact with the leading edge body 22, for example with the locking element 34 of the leading edge body 22, in order to limit the displacement of the distal edge 52 relative to the leading edge body 22.

[0092] In the above-mentioned example not shown, where the guide passages 56 are formed by both elongated holes and notches, the displacement of the cover panel 46 relative to the leading edge slat body 22 is limited, for example, by the length of the elongated holes forming the guide passages 56. For example, the guide elements 30 arranged in guide passages 56 formed by notches fasten the inner skin 28 firmly to the outer skin 26, and the guide elements 30 arranged in guide passages 56 formed by elongated holes detachably fasten the inner skin 28 to the outer skin 26.In other words, the guide elements 30, which pass through notches, ensure the fastening of the inner skin 28 to the outer skin 26, while enabling the installation of the cover panel 46 on the leading edge slat body 16, the guide elements 30, which pass through elongated holes, can be installed after the cover panel 46 has been properly positioned relative to the leading edge slat body 22 and ensure limited displacement of the cover panel 46 relative to the leading edge slat body 22 during installation.

[0093] A method for reconfiguring a wing 14 which includes a leading edge slat 18 as described above is now presented.

[0094] The procedure includes a movement step in which the leading edge slat 18 is moved relative to the fixed wing section 16 between its extended and retracted positions.

[0095] The process further includes, for example, a deformation step in which the cover panel 46 of the leading edge slat filler device 24 is deformed between the fixed wing section 16 and the leading edge slat body 22. The deformation results, for example, from the interaction between the leading edge slat filler device 24 and the fixed wing section 16, which are moved relative to each other as a result of the movement step.

[0096] The procedure further includes a sliding step in which the distal edge 52 of the cover panel 46 of the leading edge slat filler device 24 slides relative to the leading edge body 22.

[0097] The sliding of the distal edge 52 is guided along the displacement direction S relative to the leading edge body 22, the displacement direction S being defined, as mentioned above, by the guide passages 56 of the cover panel 46.

[0098] For example, during the sliding step, the cover panel 46 slides between the inner skin 28 and the outer skin 26, so that the distal edge 52 is guided along the displacement direction S relative to the leading edge body 22.

[0099] As shown above, the use of a leading edge slat filler device 24, in which guide passages 56 are configured to guide the distal edge 52 along the displacement direction S, is particularly advantageous in order to provide a robust and aerodynamically efficient leading edge slat filler device 24.

[0100] The use of a flexible cover panel 46 is particularly advantageous because the deformation of the cover panel 46 ensures that the leading edge slat 18 can be moved relative to the fixed wing section 16, while ensuring that the leading edge slat groove 41 is filled / covered when the leading edge slat 18 is, for example, in an extended position.

[0101] Guide passages 56, which are elongated along the displacement direction S, and a displacement direction S which is perpendicular to the span direction Y, are particularly advantageous to provide proper guidance of the leading edge slat filler device 24.

[0102] Guide passages 56, which are formed by elongated holes or notches, make it possible, for example, to limit the displacement of the leading edge flap filler device 24 relative to the leading edge flap body 22.

[0103] The use of a limiting element 48, for example an elastic tongue 58 and / or a locking element 34, is particularly advantageous for robustly and / or gently limiting the displacement of the leading edge slat filler 24 relative to the leading edge slat body 22. The elastic tongue 58 is also advantageous because it can deform elastically to allow the installation of the leading edge slat filler 24 in the leading edge slat body 22 before the elastic tongue 58 actually acts as a limiting element 48, thus improving ease of installation.

[0104] The sliding of the cover panel 46 between the inner skin 28 and the outer skin 26 is particularly advantageous in order to further improve the accuracy of the guidance.

[0105] The use of at least one guide element 30, which connects the inner skin 28 and the outer skin 26, makes the assembly of the leading edge flap 18 particularly easy.

[0106] The spacer 32, which is arranged between the inner skin 28 and the outer skin 26, ensures proper control of the distance between the inner skin 28 and the outer skin 26, thereby ensuring optimal sliding of the cover panel 46 relative to the leading edge body 22.

Claims

[1] Leading edge slat filler device (24) for a leading edge slat (18) of an aircraft (10), wherein the leading edge slat filler device (24) comprises a cover panel (46) extending along a span direction (Y) and comprising a proximal edge (50) configured to be attached to a leading edge body (22) of the leading edge slat (18) and a distal edge (52) configured to be displaceable relative to the leading edge body (22), wherein the cover panel (46) comprises a plurality of guide passages (56), each guide passage (56) being configured to interact with a guide element (30) of the leading edge body (22) to guide the distal edge (52) along a displacement direction (S) relative to the leading edge body (22). [2] Leading edge slat filler device (24) according to claim 1, wherein the cover panel (46) is flexible and configured to be deformable between the leading edge slat body (22) and a fixed wing section (16) of the aircraft (10) when the leading edge slat body (22) is displaced relative to the fixed wing section (16) of the aircraft (10). [3] Leading edge filler device (24) according to claim 1 or 2, wherein the guide passages (56) are elongated along the displacement direction (S), wherein the displacement direction (S) is substantially perpendicular to the span direction (Y). [4] Leading edge filler device (24) according to one of the preceding claims, wherein the plurality of guide passages (56) is adjacent to the distal edge (52), wherein each guide passage (56) is formed by an elongated hole or a notch. [5] Leading edge filler device (24) according to one of the preceding claims, wherein the leading edge filler device (24) further comprises at least one limiting element (48), wherein the limiting element (48) is connected to the cover panel (46) and is configured to interact with the leading edge body (22) to limit the displacement of the distal edge (52) relative to the leading edge body (22) along the displacement direction (S). [6] Leading edge filler device (24) according to claim 5, wherein the limiting element (48) comprises an elastic tongue (58), wherein a tip (60) of the elastic tongue (58) is configured to interact with the leading edge body (22) to limit the displacement of the distal edge (52) relative to the leading edge body (22). [7] Leading edge slat (18) comprising a leading edge slat filler device (24) according to any one of claims 1 to 6 and a leading edge slat body (22), wherein the proximal edge (50) of the cover panel (46) of the leading edge slat filler device (24) is attached to the leading edge slat body (22) and the distal edge (52) of the cover panel (46) is displaceable relative to the leading edge slat body (22), wherein the leading edge slat body (22) comprises a plurality of guide elements (30), wherein each guide passage (56) of the cover panel (46) is configured to interact with one of the guide elements (30) to guide the distal edge (52) along the displacement direction (S) relative to the leading edge slat body (22). [8] Leading edge slat (18) according to claim 7, wherein the leading edge slat body (22) comprises an outer skin (26) and an inner skin (28), wherein the cover panel (46) is configured to slide between the inner (28) and the outer skin (26) such that the distal edge (52) slides relative to the leading edge slat body (22). [9] Leading slat (18) according to claim 8, wherein at least one of the guide elements (30) connects the inner (28) and the outer skin (26). [10] Leading edge slat (18) according to claim 8 or 9, wherein the leading edge slat body (22) comprises at least one spacer (32), wherein the spacer (32) is arranged between the inner skin (28) and the outer skin (26) to space the inner skin (28) away from the outer skin (26). [11] Leading edge slat (18) according to claim 10, wherein the leading edge slat body (22) comprises a plurality of spacers (32), each spacer (32) being arranged around one of the guide elements (30), each guide element (30) being configured to interact with one of the guide passages (56) through the spacer (32) to guide the distal edge (52) along the displacement direction (S) relative to the leading edge slat body (22). [12] Leading edge slat (18) according to claims 7 to 11, wherein the leading edge slat body (22) further comprises at least one blocking element (34), wherein the blocking element (34) is connected to the inner skin (28) and is configured to cooperate with the leading edge slat filler device (24) to block the displacement of the leading edge slat filler device (24) along the displacement direction (S). [13] Wing (14) comprising a leading edge slat (18) according to any one of claims 7 to 12 and a fixed wing section (16), wherein the leading edge slat (18) is movable relative to the fixed wing section (16) between an extended position and a retracted position, wherein the distal edge (52) of the cover panel (46) of the leading edge slat filler device (24) is configured to slide relative to the leading edge slat body (22) when the leading edge slat (18) is moved between its extended and retracted positions. [14] Aircraft (10) comprising a wing (14) according to claim 13. [15] Method for reconfiguring a wing (14) according to claim 13, wherein the method comprises the following steps: - Moving the leading edge slat (18) relative to the fixed wing section (16) between its extended and retracted positions, and - Sliding of the distal edge (52) of the cover panel (46) of the leading edge slat filler device (24) relative to the leading edge body (22), wherein the sliding of the distal edge (52) is guided along a displacement direction (S) relative to the leading edge body (22), wherein the displacement direction (S) is defined by the guide passages (56) of the cover panel (46).

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