Wing for aircraft, leading edge high lift assembly for wing and aircraft

Abstract

The invention relates to a wing for an aircraft, a leading edge high lift assembly for the wing and the aircraft. The wing includes a main wing and a leading edge high lift assembly including a slat and a connection assembly connecting the slat to the main wing such that the slat is movable between a retracted position, a first extended position, and a second extended position, where the connection assembly includes an elongate slat track, where the slat track is configured to be movable between a first extended position and a second extended position. A first end and / or a middle portion of the slat track is mounted to the slat, where the slat track is mounted to the main wing such that the slat track is movable along a track longitudinal axis. The object of providing a wing with a beneficial ratio of aerodynamic performance and noise resulting from the extension of the slat is achieved in that the slat track is mounted to the slat rotatable about the slat axis, and the connection assembly comprises a slat angle mechanism, a slat angle mechanism is mounted to the slat and configured to control an angle of the slat about the slat axis as the slat moves.

Description

Technical Field

[0001] This invention relates to wings for aircraft. Other aspects of the invention relate to leading-edge high-lift assemblies for such wings, and aircraft including such wings and / or including such leading-edge high-lift assemblies. Background Technology

[0002] The described wing for an aircraft includes a main wing and a leading-edge high-lift assembly. The leading-edge high-lift assembly includes slats and a connecting assembly that movably connects the slats to the main wing, allowing the slats to move relative to the main wing between a retracted position and several extended positions, particularly a first extended position and a second extended position. The first extended position preferably relates to a partially extended position taken during takeoff of the respective aircraft, while the second extended position preferably relates to a fully extended position taken during approach and landing of the respective aircraft.

[0003] The connecting assembly includes an elongated slat track extending along a longitudinal axis between a first end and a second end, and having an intermediate portion between the two ends. The slat track may be curved or straight along its longitudinal axis. At least one or both of the first end and the intermediate portion of the slat track are mounted to the slat. The first end preferably corresponds to the leading end of the slat track, for example, an end positioned in the expected direction of forward movement of the wing during flight. The first end of the slat track may preferably be mounted to the slat by any suitable means, for example by one or more ball bearings. The slat track is mounted to the main wing by roller bearings, enabling the slat track to move along its longitudinal axis, particularly along a predetermined travel path, such as between a retracted position when the slat is in a retracted position, a first deployed position when the slat is in a first extended position, and a second deployed position when the slat is in a second extended position.

[0004] The slat track can be, for example, C-shaped, with its surface facing the circumferential surface of the roller support. The distance between the upper and lower surfaces of the slat track is greater than the diameter of the roller support, allowing the roller support to engage with only one of the upper or lower surfaces of the slat track at any given time. That is, the distance between the upper and lower surfaces of the slat track is chosen such that a gap is provided between the roller support and either the upper or lower surface of the slat track, preventing the roller support from engaging with both surfaces simultaneously and thus avoiding wedging.

[0005] Similar wings are known in the prior art. Some known wings employ sealed slats, the trailing edge of which contacts the leading edge of the main wing at all points, ensuring that there is never a gap between the trailing edge of the slat and the leading edge of the main wing. Avoiding gaps reduces aerodynamic drag and noise. Other wings have slats whose trailing edge is spaced apart from the leading edge of the main wing by gaps at all points where the slat extends. Such gaps guide fresh air from under the wing to the upper side, thus suppressing flow separation and therefore increasing lift. Summary of the Invention

[0006] Therefore, the object of the present invention is to provide a wing having a beneficial ratio of aerodynamic performance and noise generated by the extension of slats.

[0007] This objective is achieved by mounting a slat track to a slat capable of rotating about its axis. The slat axis preferably extends along the wingspan and / or parallel to the trailing edge of the slat and / or parallel to the leading edge of the main wing and / or perpendicular to the longitudinal axis of the track. Furthermore, the connecting assembly includes a slat angle mechanism mounted to the slat, preferably fixedly mounted to the slat, and preferably mounted to the main wing, wherein the slat angle mechanism is configured to control the angle of the slat about its axis as the slat moves between a retracted position, a first extended position, and a second extended position. By controlling the angle of the slat about its axis, the position of the trailing edge of the slat relative to the leading edge of the main wing can be controlled throughout the entire movement path of the slat between the retracted position, the first extended position, and the second extended position. That is, it is possible to control at what position along the movement path of the slat that the trailing edge of the slat rests against the leading edge of the main wing, thereby restricting fluid flow between the slat and the main wing, and at what position a gap is formed between the trailing edge of the slat and the leading edge of the main wing to allow fluid flow. In this way, the resulting lift, drag, and noise can be modulated to some extent along the slat's path of motion between the retracted position, the first extended position, and the second extended position, thus being most favorable for cruise flight, takeoff, and approach and landing. This means that an ideal ratio of aerodynamic performance to noise generated by the slat's extension can be achieved.

[0008] According to a preferred embodiment, the slat angle mechanism is configured to control the angle of the slat about its axis, such that in the retracted position and the first extended position, the slat rests against the main wing, particularly the trailing edge of the slat against the leading edge of the main wing, preventing fluid from passing between the slat and the main wing. In the second extended position, a gap is formed between the trailing edge of the slat and the leading edge of the main wing to allow fluid to pass through. In this way, the advantages of a sealed slat and the advantages of a slat configuration with a gap are combined. Specifically, for takeoff during aircraft acceleration, low drag and low noise are desired, therefore the closed gap in the first extended position is advantageous. The same applies to cruise flight. For approach and landing, conversely, when the aircraft requires high lift to reach minimum speed, the gap in the fully extended position of the slat is advantageous. In this way, an ideal ratio of aerodynamic performance to noise resulting from the extension of the slat is achieved.

[0009] According to another preferred embodiment, the slat angle mechanism includes a slat angle rod and a rod guide. The slat angle rod is mounted to the slat, preferably fixedly mounted to the slat, preferably mounted to the slat through one end, and guided by the rod guide, preferably guided by the rod guide through its other end. The rod guide is preferably mounted to the main wing. In this way, a simple and effective slat angle mechanism is provided.

[0010] In particular, preferably, the rod guide is formed as a rod guide rail, and the slat angle rod includes slat angle rollers that engage with the rod guide rail to roll along the rod guide rail in a guided manner. In this way, a simple, reliable, and efficient slat angle mechanism is provided.

[0011] A further preferred embodiment is that the rod guide forms a guide path along which the slat angle rod is guided. The guide path is configured such that the slat angle rod controls the angle of the slat about the slat axis, such that in the retracted position and the first extended position, the trailing edge of the slat rests against the leading edge of the main wing, while in the second extended position, a gap is formed between the trailing edge of the slat and the leading edge of the main wing to allow fluid passage. To achieve this, the guide path can be straight or curved, depending on the form of the slat, the main wing, the slat track, and their travel paths. In this way, a simple and effective slat angle mechanism is provided.

[0012] According to a preferred embodiment, the slat angle mechanism is arranged in the same chordal plane as the slat track, i.e., in the same span layer, meaning it is at the same level in the spanwise direction. In this way, the cutout in the leading edge panel of the main wing can have a minimal size.

[0013] In particular, it is preferable that the slat angle mechanism is positioned above or below the slat track relative to the normal position of the aircraft on the ground, that is, in front of or behind the slat track when viewed along the thickness direction of the wing. This relates to a spatially efficient arrangement that allows for effective adjustment of the slat angle.

[0014] Further preferably, the slat track is configured to provide space for the slat angle mechanism, and in particular for the slat angle rod, to be arranged and moved adjacent to the slat track, including contact with the slat track, so as to allow for minimal required space by the slat track and the slat angle mechanism, and therefore minimal required cutouts in the leading edge panel of the main wing.

[0015] Particularly preferred is that the slat track has a cross-sectional shape spanning the longitudinal axis of the track, comprising first and second side portions spaced apart from each other in the wingspan direction, and a connecting portion connecting the first and second side portions to form at least one cavity partially surrounded by the first and second side portions and the connecting portion. This shape can be, for example, H-shaped, U-shaped, or Π-shaped. The cavity preferably extends elongatedly parallel to the longitudinal axis of the track. The cavity opens upward and / or downward relative to the normal position of the associated aircraft on the ground. The slat angle mechanism, particularly the slat angle rod, extends at least partially within the cavity and preferably moves within the cavity relative to the slat track, for example, in a direction substantially parallel to the longitudinal axis of the track. In this way, a very compact arrangement is provided, which can result in minimal cutouts in the leading edge panel of the main wing.

[0016] According to an alternative preferred embodiment, the slat angle mechanism is arranged in a chordal plane different from the slat track, i.e., offset from the slat track relative to the wingspan direction. This arrangement may be advantageous, for example, due to space constraints in the chordal plane of the slat track.

[0017] According to a preferred embodiment, the roller support includes at least two, preferably three, roller units mounted to the main wing and configured to engage with corresponding engagement surfaces at the slat track. The engagement surfaces may be located on the upper and / or lower surface of the slat track, such that the engagement surfaces are opposite to each other, or the engagement surfaces may be disposed in recesses formed in one or both lateral sides of the slat track, such that the engagement surfaces face each other. In this way, a very simple, compact, reliable, and effective roller support is provided.

[0018] According to an alternative preferred embodiment, the roller support includes a first roller unit mounted to a second end, i.e., the rear end, of the slat track and configured to engage with a guide rail mounted to, and preferably fixedly mounted to, the main wing. The roller support also includes a second roller unit mounted to, and preferably fixedly mounted to, the main wing and configured to engage with a corresponding engagement surface at the slat track. The engagement surfaces may, for example, be located on the upper and / or lower surface of the slat track, such that the engagement surfaces are opposite to each other, or the engagement surfaces may be disposed in a recess formed in one or both lateral sides of the slat track, such that the engagement surfaces face each other. In this way, an alternative, simple, compact, reliable, and effective roller support is provided.

[0019] According to another preferred embodiment, the wing further includes a drive unit mounted to the main wing and coupled to a slat track for moving the slat track and thus the slats between a retracted position, a first extended position, and a second extended position. The drive unit preferably includes a drive pinion mounted to the main wing, for example driven by a motor, and engaging a rack disposed at the slat track. Alternatively, the drive unit includes a drive linkage mechanism comprising at least one drive link and driven by a rotary actuator or linear actuator mounted at the main wing. In this way, a simple, reliable, and efficient drive unit is provided.

[0020] Another aspect of the invention relates to a leading-edge high-lift assembly for a wing according to any of the embodiments described above. The leading-edge high-lift assembly includes a slat and a connecting assembly configured to movably connect the slat to the main wing, such that the slat is movable between a retracted position, a first extended position, and a second extended position. The connecting assembly includes a slat track extending along a longitudinal axis between a first end and a second end and having an intermediate portion between the first end and the second end. The first end and / or the intermediate portion of the slat track can be configured to be mounted to the slat. The slat track can be configured to be mounted to the main wing via roller supports, such that the slat track is movable along the longitudinal axis of the track. The slat track can be configured to be mounted to a slat capable of rotating about a slat axis. The connecting assembly includes a slat angle mechanism configured to be mounted to the slat and configured to control the angle of the slat about the slat axis as the slat moves between the retracted position, the first extended position, and the second extended position. The aforementioned wing-related features and effects also apply to the leading-edge high-lift assembly.

[0021] Another aspect of the invention relates to an aircraft comprising a wing according to any of the embodiments described above, and / or including a leading-edge high-lift assembly according to the embodiments described above. The features and effects described above related to the wing and the leading-edge high-lift assembly also apply to the aircraft. Attached Figure Description

[0022] In the following, preferred embodiments of the invention will be explained in more detail with the aid of the accompanying drawings. The drawings are shown as follows:

[0023] Figure 1 This is a perspective view of the aircraft according to the present invention.

[0024] Figure 2a , Figure 2b and Figure 2c These are three side views of a wing according to an embodiment of the present invention, wherein the slats are in a retracted position, a first extended position, and a second extended position.

[0025] Figure 3 This is a side view of a wing according to another embodiment of the present invention, and

[0026] Figure 4 yes Figure 3 The schematic side view shown depicts the wing moving between the retracted position, the first extended position, and the second extended position. Figure 4 Two cross-sectional views of the slat track and slat angle rod at different positions along the longitudinal axis of the track. Detailed Implementation

[0027] exist Figure 1 The figure shows an aircraft 1 according to an embodiment of the present invention. The aircraft 1 includes a fuselage 2, wings 3 and a tail unit 4. Each wing 3 includes a main wing 5 and a leading-edge high-lift assembly 6, the leading-edge high-lift assembly 6 including a slat 7 and a connecting assembly 9, the connecting assembly 9 connecting the slat 7 to the main wing 5, such that the slat 7 can move relative to the main wing 5.

[0028] like Figure 1 As shown, the connecting component 9 relates to a first connecting component 91, and the wing 3 includes a second connecting component 93 that connects the slat 7 to the main wing 5 at a position spaced apart from the first connecting component 91 along the wingspan direction 95, and wherein the second connecting component 93 is formed in the same manner as the first connecting component 91.

[0029] Figures 2a to 4 The illustrations show two embodiments of the wing 3 according to the invention, for example, which can be used in... Figure 1 The aircraft 1 shown in the image.

[0030] Figures 2a to 2cThe illustration shows a wing 3 according to a first embodiment of the present invention. (As shown in the diagram...) Figure 1 As indicated, wing 3 includes a main wing 5 and a leading-edge high-lift assembly 6. The leading-edge high-lift assembly 6 includes a slat 7 and a connecting assembly 9, which connects the slat 7 to the main wing 5, such that the slat 7 can be in a retracted position 11 relative to the main wing 5. Figure 2a (as shown in the image), first extended position 13 ( Figure 2b (as shown in the image) and the second extension position 15 ( Figure 2c The aircraft moves between the retracted position 11 and the extended position 13, which is a partially extended position intended for takeoff, and the extended position 15, which is a fully extended position intended for approach and landing of the associated aircraft 1.

[0031] The connecting assembly 9 includes a slat track 17 that extends along a longitudinal axis 19 between a first end 21 and a second end 23, and has an intermediate portion 25 located therebetween. In this embodiment, the slat track 17 has a curved form along the longitudinal axis 19, but in other embodiments it may have a straight form. In this example, the slat 7 is mounted to the first end 21 of the slat track 17, although it may also be mounted to the intermediate portion 25, either additionally or alternatively. The slat track 17 is mounted to the main wing 5 via a roller support 27. The roller support 27 allows the track 17 to move relative to the main wing 5 along the longitudinal axis 19, and thus also allows the slat 7 to move relative to the main wing 5 between a retracted position 11, a first extended position 13, and a second extended position 15.

[0032] A slat track 17 is mounted to a slat 7, which is rotatable about a slat axis 22. The slat axis 22 extends along the wingspan direction 95 and / or parallel to the trailing edge of the slat 7 and / or parallel to the leading edge of the main wing 5 and / or perpendicular to the longitudinal axis 19 of the track. Furthermore, the connecting assembly 9 includes a slat angle mechanism 10 mounted to both the slat 7 and the main wing 5, wherein the slat angle mechanism 10 is configured to control the angle of the slat 7 about the slat axis 22 as the slat 7 moves between a retracted position 11, a first extended position 13, and a second extended position 15. Specifically, the slat angle mechanism 10 is configured to control the angle of the slat 7 about the slat axis 22 such that in the retracted position 11 and the first extended position 13, the trailing edge of the slat 7 rests against the leading edge of the main wing 5, preventing fluid from passing between the slat 7 and the main wing 5, while in the second extended position 15, a gap 26 is formed between the trailing edge of the slat 7 and the leading edge of the main wing 5 to allow fluid to pass through.

[0033] like Figures 2a to 2cAs shown, the slat angle mechanism 10 includes a slat angle rod 29 and a rod guide 31. The slat angle rod 29 is mounted to the slat 7 and guided by the rod guide 31, which is mounted to the main wing 5. The rod guide 31 is formed as a rod rail 32, and the slat angle rod 29 includes slat angle rollers 33 that engage the rod rail 32 to roll along it in a guided manner. The rod guide 31 forms a guide path 35 along which the slat angle rod 29 is guided, wherein the guide path 35 is configured such that the slat angle rod 29 controls the angle of the slat 7 about the slat axis 22, such that in the retracted position 11 and the first extended position 13, the trailing edge of the slat 7 rests against the leading edge of the main wing 5, and in the second extended position 15, a gap 26 is formed between the trailing edge of the slat 7 and the leading edge of the main wing 5. Figure 2a , Figure 2b and Figure 2c In the embodiment shown, the guide path 35 is in a straight line, but in other embodiments, such as in... Figure 3 In the embodiment shown, the guide path 35 is not straight, but curved and / or twisted, depending on the form of the slat 7, the main wing 5, and the slat track 17 and their travel paths.

[0034] exist Figure 2a , Figure 2b , Figure 2c and Figure 3 In the embodiment shown, the slat angle mechanism 10 is arranged in the same chordal plane as the slat track 17. However, in other embodiments, the slat angle mechanism 10 may also be arranged in a different chordal plane than the slat track 17, i.e., offset from the slat track 17 relative to the wingspan direction 95. The chordal plane is spanned by the thickness direction 67 and the chordal direction 97 of the wing 3. Figure 2a , Figure 2b , Figure 2c and Figure 3 In the embodiment shown, the slat angle mechanism 10 is positioned above the slat track 17 relative to the normal position of the associated aircraft 1 on the ground, that is, in front of the slat track 17 when viewed along the thickness direction 67 of the wing 3. However, in other embodiments, the slat angle mechanism 10 may be positioned below the slat track 17 relative to the normal position of the associated aircraft 1 on the ground, that is, behind the slat track 17 when viewed along the thickness direction 67 of the wing 3.

[0035] like Figure 3 and Figure 4In the embodiment shown, the slat track 17 is shaped to provide space for the slat angle mechanism 10, and particularly for the slat angle rod 29, to be arranged and moved adjacent to or in contact with the slat track 17, allowing for the minimum required space provided by the slat track 17 and the slat angle mechanism 10, and therefore the minimum required cutout in the leading edge panel of the main wing 5. Figure 4 As illustrated, the slat track 17 has a cross-sectional shape spanning the longitudinal axis 19 of the track, including a first side portion 39 and a second side portion 41 spaced apart from each other in the spanwise direction 95, and a connecting portion 43. The connecting portion 43 connects the first side portion 39 and the second side portion 41 to form at least one cavity 49 partially surrounded by the first side portion 39, the second side portion 41, and the connecting portion 43. Figure 4 In the embodiments shown, depending on the position of the cross-section along the longitudinal axis 19 of the track, the form is either H-shaped or U-shaped. The cavity 49 extends elongatedly parallel to the longitudinal axis 19 of the track. The cavity 49 opens upwards relative to the normal position of the corresponding aircraft 1 on the ground. Figure 4 As can be seen, the slat angle rod 29 extends at least partially within the cavity 49 and moves within the cavity 49 relative to the slat track 17.

[0036] like Figure 2a , Figure 2b , Figure 2c and Figure 3 As shown, the roller support 27 includes at least two roller units 53 arranged at intervals along the travel path of the slat track 17 along the longitudinal axis 19 of the track, in particular Figure 2a , Figure 2b and Figure 2c The three roller units 53 in the implementation method and Figure 3 The two roller units 53 in the embodiment. Figure 2a , Figure 2b and Figure 2c In the embodiment shown, the roller unit 53 is mounted to the main wing 5 and configured to engage with the corresponding engagement surface 55 at the slat track 17. Figure 2a , Figure 2b and Figure 2c In this embodiment, the mating surface 55 is disposed in a recess 57 formed in one or both lateral sides of the slat track 17. Specifically, the mating surface 55 is disposed on the inner surfaces of the upper flange 59 and the lower flange 61 surrounding the recess 57, such that the two opposing portions of the mating surface 55 face each other. Figure 3In the embodiment shown, the roller support 27 includes a first roller unit 63 mounted to a second end 23 of the slat track 17 and configured to engage with a guide rail 69 mounted to the main wing 5. The roller support 27 also includes a second roller unit 65 mounted to the main wing 5 and configured to engage with a corresponding engagement surface 55 at the slat track 17. The engagement surface 55 is disposed between an upper flange 59 and a lower flange 61 in a recess 57 formed in one or both lateral sides of the slat track 17, such that opposing portions of the engagement surfaces 55 face each other.

[0037] like Figure 2a , Figure 2b and Figure 2c As shown, the wing 3 also includes a drive unit 71, which is mounted to the main wing 5 and connected to the slat track 17 for moving the slat track 17 and thus the slat 7 between a retracted position 11, a first extended position 13, and a second extended position 15. In this embodiment, the drive unit 71 includes a drive pinion 73, which is mounted to the main wing 5 in a driven manner and engages with a rack 75 disposed on the slat track 17. In other embodiments, the drive unit 71 may also include a drive linkage mechanism driven by a rotary actuator or linear actuator mounted on the main wing 5.

[0038] By means of the wing 3 and leading-edge high-lift assembly 6 according to the present invention and as described above, the generated lift, drag, and noise can be adjusted along the movement path of the slat 7 between the retracted position 11, the first extended position 13, and the second extended position 15, thereby being most advantageous for the corresponding flight conditions of cruise flight, takeoff, approach, and landing. This means that, for the corresponding flight conditions, an ideal ratio of aerodynamic performance to noise generated by the extension of the slat 7 can be obtained.

Claims

1. A wing (3) for an aircraft (1), comprising: Main wing (5), and Leading edge high-lift assembly (6), the leading edge high-lift assembly (6) comprising: slats (7), and A connecting assembly (9) movably connects the slat (7) to the main wing (5), allowing the slat (7) to move between a retracted position (11), a first extended position (13), and a second extended position (15). The connecting assembly (9) includes an elongated slat track (17) that extends along the longitudinal axis (19) between a first end (21) and a second end (23) and has an intermediate portion (25) between the first end (21) and the second end (23). The first end (21) and / or the middle portion (25) of the slat track (17) are mounted to the slat (7). The slat track (17) is mounted to the main wing (5) via a roller support (27), allowing the slat track (17) to move along the longitudinal axis (19) of the track. Its features are, The slat track (17) is mounted to the slat (7) which is capable of rotating about the slat axis (22). The connecting assembly (9) includes a slat angle mechanism (10) which is mounted to the slat (7) and configured to control the angle of the slat (7) about the slat axis (22) as the slat (7) moves between the retracted position (11), the first extended position (13) and the second extended position (15).

2. The wing (3) according to claim 1, wherein, The slat angle mechanism (10) is configured to control the angle of the slat (7) about the slat axis (22) such that in the retracted position (11) and in the first extended position (13), the slat (7) rests against the main wing (5), and in the second extended position (15), a gap (26) is formed between the trailing edge of the slat (7) and the leading edge of the main wing (5).

3. The wing (3) according to claim 1 or 2, wherein, The slat angle mechanism (10) includes a slat angle rod (29) and a rod guide (31). The slat angle rod (29) is installed on the slat (7) and guided by the rod guide (31). The rod guide (31) is installed on the main wing (5).

4. The wing (3) according to claim 3, wherein, The rod guide (31) is formed as a rod guide (32), and the slat angle rod (29) includes a slat angle roller (33) that engages the rod guide (32).

5. The wing (3) according to claim 3 or 4, wherein, The rod guide (31) forms a guide path (35) along which the slat angle rod (29) is guided, wherein the guide path (35) is configured such that the slat angle rod (29) controls the angle of the slat (7) about the slat axis (22), such that in the retracted position (11) and in the first extended position (13), the slat (7) rests against the main wing (5), and in the second extended position (15), a gap (26) is formed between the trailing edge of the slat (7) and the leading edge of the main wing (5).

6. The wing (3) according to any one of claims 1 to 5, wherein, The slat angle mechanism (10) is arranged in the same chord plane as the slat track (7).

7. The wing (3) according to claim 6, wherein, The slat angle mechanism (10) is arranged above or below the slat track (17).

8. The wing (3) according to claim 6 or 7, wherein, The form of the slat track (17) is adapted to provide space for the slat angle mechanism (10) to be arranged and moved adjacent to the slat track (17).

9. The wing (3) according to claim 8, wherein, The slat track (17) has a cross-sectional shape comprising a first side portion (39) and a second side portion (41) spaced apart from each other in the spanwise direction (95) and a connecting portion (43) connecting the first side portion (39) and the second side portion (41) to form at least one cavity (49) partially surrounded by the first side portion (39), the second side portion (41) and the connecting portion (43). The cavity (49) is open in the upward and / or downward direction. The slat angle mechanism (10) extends at least partially within the cavity (49).

10. The wing (3) according to any one of claims 1 to 5, wherein, The slat angle mechanism (10) is arranged in a chord plane different from that of the slat track (17).

11. The wing (3) according to any one of claims 1 to 10, wherein, The roller support (27) includes at least two roller units (53) mounted to the main wing (5) and configured to engage with a corresponding engagement surface (55) at the slat track (17).

12. The wing (3) according to any one of claims 1 to 10, wherein, The roller support (27) includes a first roller unit (63) mounted to the second end (23) of the slat track (17) and configured to engage with a guide rail (69) mounted to the main wing (5), and a second roller unit (65) mounted to the main wing (5) and configured to engage with a corresponding engagement surface (55) at the slat track (17).

13. The wing (3) according to any one of claims 1 to 12, wherein, The wing (3) also includes a drive unit (71) which is mounted to the main wing (5) and connected to the slat track (17) for moving the slat track (17) and thus the slat (7) between the retracted position (11), the first extended position (13), and the second extended position (15). The drive unit (71) includes a drive pinion (73) mounted to the main wing (5) and engaging with a rack (75) disposed on the slat track (17), or includes a drive linkage mechanism comprising at least one drive link and driven by a rotary actuator or linear actuator mounted on the main wing (5).

14. A leading-edge high-lift assembly (6) for a wing (3), said wing (3) being a wing (3) according to any one of claims 1 to 13, said leading-edge high-lift assembly (6) comprising: slats (7), and A connecting assembly (9) configured to movably connect the slat (7) to the main wing (5) such that the slat (7) is movable between a retracted position (11), a first extended position (13), and a second extended position (15). The connecting assembly (9) includes a slat track (17) that extends along the longitudinal axis (19) between a first end (21) and a second end (23) and has an intermediate portion (25) between the first end (21) and the second end (23). The first end (21) and / or the middle portion of the slat track (17) can be configured to be mounted to the slat (7). The slat track (17) can be configured to be mounted to the main wing (5) via a roller support (27), so that the slat track (17) can move along the longitudinal axis (19) of the track. Its features are, The slat track (17) can be configured to be mounted on the slat (7) which is rotatable about the slat axis (22), and The connecting assembly (9) includes a slat angle mechanism (10) which is configured to be mounted to the slat (7) and to control the angle of the slat (7) about the slat axis (22) as the slat (7) moves between the retracted position (11), the first extended position (13) and the second extended position (15).

15. An aircraft (1) comprising a wing (3) according to any one of claims 1 to 13 and / or comprising a leading-edge high-lift assembly (6) according to claim 14.

Images