SYSTEM FOR DRIVING A SLAT DEVICE OF AN AIRCRAFT WING

Abstract

Disclosed herein is an exemplary embodiment of a system for driving a slat of an aircraft. The system includes first and second hinge support elements of a wing structure, a first arm device, a second arm device, and a third arm device. Also disclosed is an aircraft having the system, an aircraft wing having the system, and a method for driving a slat of an aircraft. The system utilizes a particular configuration of connection junctions, which rotatably connect the arm devices and the hinge support elements.

Claims

1. A system for driving a slat of an aircraft, comprising: a first hinge support element of an aircraft wing structure; a second hinge support element of the aircraft wing structure; a first arm device; a second arm device; and a third arm device; wherein the first arm device is rotatably connected by an associated first connection junction to the first hinge support element, comprising a second connection junction configured to be rotatably connected to a rear portion of the slat, having a steady curved shape between the first connection junction and the second connection junction, and comprising a third connection junction arranged between the first and second connection junction, of the first arm device; wherein the second arm device is linearly extendable, being rotatably connected by an associated first connection junction to the second hinge support element, comprising a second connection junction being configured to be rotatably connected to a front portion of the slat, and comprising a third connection junction arranged between the first and second connection junction, of the second arm device; and wherein the third arm device is rotatably connected by an associated first connection junction to the third connection junction of the first arm device, and being rotatably connected by an associated second connection junction to the third connection junction of the second arm device.

2. The system according to claim 1, wherein the first arm device comprises a J-shaped cross profile or an L-shaped cross profile.

3. The system according to claim 2, wherein the second arm device comprises a first shaft element and a second shaft element, and wherein the first and second shaft elements are connected by a linear guide mechanism configured to provide a translational shift between the first and second shaft elements, such that the second arm device is translationally and/or linearly extendable.

4. The system according to claim 3, wherein the first shaft element is rotatably connected by the associated first connection junction to the second hinge support element and comprises the associated third connection junction, and wherein the second shaft element comprises the associated second connection junction.

5. The system according to claim 1, wherein the first arm device is rotatable about the first hinge support element at least between a first pivot position and a second pivot position, wherein in the first pivot position, the system is configured to arrange the slat in a retracted position within an aircraft wing, such that a forward leading edge of the slat is forward of a rear trailing edge of the slat.

6. The system according to claim 5, wherein in the second pivot position of the first arm device, the system is configured to arrange the slat in an operation position outside the aircraft wing, such that the rear trailing edge of the slat is forward of a forward leading edge of the aircraft wing or is arranged above and in overlap with the forward leading edge of the aircraft wing.

7. The system according to claim 6, wherein the system is configured to drive the slat from the retracted position to the operation position along a trajectory, such that the forward leading edge of the slat is constantly forward of the rear trailing edge of the slat.

8. The system according to claim 1, wherein the first arm device comprises a fourth connection junction, wherein the system comprises a fourth arm device being rotatably connected by an associated first connection junction to the fourth connection junction of the first arm device, and wherein the fourth arm device comprises a second connection junction being configured to be rotatably connected to the bottom panel of the aircraft wing.

9. An aircraft wing for an aircraft, comprising: an aircraft wing structure; a slat; and a system comprising: a first hinge support element of an aircraft wing structure; a second hinge support element of the aircraft wing structure; a first arm device; a second arm device; and a third arm device; wherein the first arm device is rotatably connected by an associated first connection junction to the first hinge support element, comprising a second connection junction configured to be rotatably connected to a rear portion of the slat, having a steady curved shape between the first connection junction and the second connection junction, and comprising a third connection junction arranged between the first and second connection junction, of the first arm device; wherein the second arm device is linearly extendable, being rotatably connected by an associated first connection junction to the second hinge support element, comprising a second connection junction being configured to be rotatably connected to a front portion of the slat, and comprising a third connection junction arranged between the first and second connection junction, of the second arm device; wherein the third arm device is rotatably connected by an associated first connection junction to the third connection junction of the first arm device, and being rotatably connected by an associated second connection junction to the third connection junction of the second arm device; wherein the first and second hinge support elements are arranged within the aircraft wing and attached to the aircraft wing structure; wherein the second connection junction of the first arm device is rotatably connected to the rear portion of the slat; and wherein the second connection junction of the second arm device is rotatably connected to a front portion of the slat.

10. The aircraft wing according to claim 9, wherein the first hinge support element is arranged at a first internal, forward leading section of the aircraft wing structure, and wherein the second hinge support element is arranged rearward the first section of the aircraft wing structure at a second internal section of the aircraft wing structure.

11. The aircraft wing according to claim 9, wherein the aircraft wing comprises a bottom panel, wherein the system is configured to move, in particular pivot, the bottom panel from a closed position to an open position before or while rotating the first arm device from the first pivot position to the second pivot position.

12. An aircraft comprising a system according to claim 1 or an aircraft wing according to claim 9.

13. A method for driving a slat of an aircraft, comprising the steps of: (a) driving the slat out of a lower opening of an aircraft wing in a downward and forward movement; (b) driving the slat thereafter in an upward and forward movement in front of the aircraft wing; and (c) driving the slat thereafter in an upward and backward movement.

14. The method according to claim 13, wherein the forward leading edge remains forward to a rear trailing edge during the driving steps (a), (b) and (c).

15. The method according to claim 13, wherein at least in step (b) and/or in step (c), the movement of the slat further comprises a rotation component in order to decrease an angle of attack of the slat.

16. The method according to claim 15, wherein a larger decrease of the angle of attack is performed during step (b) than during step (a) and/or step (c).

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0056] Additional features, advantages and possible applications of the disclosed subject matter may be gleaned from the following description of the exemplary embodiments and the figures. Furthermore, the same reference signs in the figures denote the same or similar objects.

[0057] FIG. 1 schematically illustrates in a first example the aircraft wing comprising the system in a cross-sectional view.

[0058] FIG. 2 schematically illustrates in a further example the aircraft wing comprising the system in a cross-sectional view.

[0059] FIG. 3 schematically illustrates in a further example the aircraft wing comprising the system in a cross-sectional view.

[0060] FIG. 4 schematically illustrates in a further example the aircraft wing comprising the system in a perspective view.

[0061] FIG. 5 schematically illustrates in a further example the aircraft wing comprising the system in a cross-sectional view.

[0062] FIG. 6 schematically illustrates in a further example the aircraft wing comprising the system in a cross-sectional view.

[0063] FIG. 7 schematically illustrates in a further example the aircraft wing comprising the system in a cross-sectional view.

[0064] FIG. 8 schematically illustrates in a further example the aircraft wing comprising the system in a cross-sectional view.

[0065] FIG. 9 schematically illustrates a lock mechanism for the bottom panel of the aircraft wing comprising in a cross-sectional view.

[0066] FIG. 10 schematically illustrates an example of an aircraft comprising an aircraft wing in a top-view.

DETAILED DESCRIPTION

[0067] The following detailed description is merely illustrative in nature and is not intended to limit the embodiments of the subject matter or the application and uses of such embodiments. As used herein, the word “exemplary” means “serving as an example, instance, or illustration.” Any implementation described herein as exemplary is not necessarily to be construed as preferred or advantageous over other implementations. Furthermore, there is no intention to be bound by any expressed or implied theory presented in the preceding technical field, background, brief summary or the following detailed description.

[0068] FIG. 1 shows a part of an aircraft wing 2 in a schematic cross-sectional view. The aircraft wing 2 as such comprises an upper surface panel 4, a leading edge surface panel 6 and a lower surface panel 8. The panels 4, 6, 8 may be continuously or separately formed. The upper surface panel 4 forms an upper surface 10 of the aircraft wing 2. The lower surface panel 8 forms a lower surface 12 of the aircraft wing 2. It is to be understood that the aircraft wing 2 may be constructed in a conventional and/or arbitrary manner. In particular, the aircraft wing 2 may comprise spanwise-oriented wing spars (not shown) located within the aircraft wing 2. Further, the aircraft wing 2 may comprise ribs (not shown) extending between the wing spars, in particular at spaced intervals along a spanwise dimension of the aircraft wing 2. The upper surface panel 4, the leading edge surface panel 6, the lower surface panel 8, the wing spars and/or the ribs may form or may be a part of the wing structure 14 of the aircraft wing 2. The wing structure 14 may also be referred to as the aircraft wing structure.

[0069] As shown in FIG. 1, there is also schematically illustrated a slat 16 and a system 18 for driving the slat 16. The slat 16 is preferably formed as a rigid slat. The slat 16 comprises an upper surface panel 20, a lower surface panel 22, a forward leading edge 24 and a rear trailing edge 26, which may be separately or integrally formed. In particular, one of the panels may be integrally formed with one of the edges.

[0070] As illustrated in FIG. 1, the slat 16 may be arranged within the aircraft wing 2. This position of the slat 16 is referred to as the retracted position of the slat 16. In order to increase the lift coefficient, in particular during take-offs and landings, the slat 16 is to be arranged forward of the leading edge 6 of the aircraft wing 2, as it is exemplarily shown in FIG. 5, preferably such that a gap 28 is formed between the leading edge 6 of the aircraft wing 2 and the rear trailing edge 26 of the slat 16. The gap 28 allows an energy-rich stream of air to move from the flow approaching the aircraft wing 2 onto the upper surface panel 4, where it shifts the stall towards higher angles of attack. In FIG. 5, the position of the slat 16 is referred to as an example of the operation position of the slat 16. As can be seen from the FIGS. 1 and 5, the system 18 is configured to drive the slat 16 from the retracted position to the operation position, and vice versa.

[0071] The FIGS. 2 and 3 show states and positions of the system 18 and the slat 16, respectively, during the movement of the slat 16 between its retracted position and operation position. From the combination of the FIGS. 1, 2, 3 and 5 it can be taken that the system 18 is configured to drive the slat 16 along a trajectory, such that the forward leading edge 24 of the slat 16 is constantly forward of the rear trailing edge 26 of the slat 16. This movement prevents that the slat 16 is positioned broadside in the airstream and therefore allows to drive the slat 16 with low power requirements for the system 18. In particular, FIG. 3 shows that angle of attack α between an air stream direction A and a chord line C of the slat 16 is smaller than 90°, which otherwise would correspond to broadside orientation of the slat 16.

[0072] In order to ensure a decrease of the angle of attack during the last third of the movement of the slat 16 from the retracted position to the operating position, the system comprises a first, single piece, curved shaped arm device 30, which is also referred to as the first arm device 30. Preferably, the curved shaped arm device 30 is J-shaped or L-shaped. Thus, the curved shaped arm device 30 does not necessarily have a constant curvature. Instead, the curved shaped arm device 30 may be curved at least at its last third end section, where the first connection junction 50 is located. Further, a mean curvature of a first third end section of the arm device 30 may be smaller than a mean curvature of the last third end section of the first arm device 30. Further, the curved shaped arm device 30 may be arched shaped. The first arm device 30 is rotatably connected to the aircraft wing structure 14, such that a corresponding pivotable end 32 may be rotated between a first pivot position, as exemplarily shown in FIG. 1, being arranged within the aircraft wing 2 and a second pivot position, as exemplarily shown in FIG. 5, at least partly encompassing the leading edge 6 of the aircraft wing 2 to be arranged in front of it. The curved shape of the first arm device 30 is preferably formed as an approximate J-shape. As a result, the curved shape of the first arm device 30 prevents a collision with the leading edge surface panel 6 of the aircraft wing 2 during the explained movement of the slat 16.

[0073] The curved shape of the first arm device 30 may provide the effect that the slat 16 may be moved during the last third, in particular during the last fifth, of the deployment movement of a slat 16 between the retracted position and the operating position, such that the rear trailing edge 26 of the slat 16 is moved upward above the leading edge of the aircraft wing 2. As a result, the forward leading edge 24 may also be moved upward during said last third, in particular during the last fifth, of the deployment movement, such that an enhanced flow, in particular an enhanced laminar flow, may be provided.

[0074] Further, the curved shape of the first arm device 30 may provide the effect that the slat 16 may be moved during the last third, in particular during the last fifth, of the deployment movement of a slat 16 between the retracted position and the operating position, such that the rear trailing edge 26 of the slat 16 is in overlap with the leading edge surface panel 6 of the aircraft wing 2, because the first arm device 30 may, due to its curvature, encompass the leading edge surface panel 6 of the aircraft wing 2 at least partly. As a result, the slat 16 may be subject to a backward movement during the previously-mentioned last third or fifth of the deployment movement. As a consequence, the lift coefficient may be increased.

[0075] Furthermore, the system 18 is preferably configured such that a change of the angle of attack α of the slat 16 with respect to the air stream direction A is higher during the second third of the deployment movement than during the first third of the deployment movement or the last third of the deployment movement. Further, the change of the angle of attack α of the slat 16 with respect to the air stream direction A may be kept small, in particular smaller than 40°, during the first and/or last third of the deployment movement of the slat 16. As an effect, a rather translational movement may be performed at the first and/or last third of the deployment movement of the slat 16. This allows to drive the slat 16 out of the aircraft wing 2 during the first third of the deployment movement.

[0076] The system further comprises a second, linearly extendable arm device 36, which is also referred to as the second arm device 36. The second arm device 36 is rotatably connected to the aircraft wing structure 14 and linked to the first arm device 30 via a third arm device 38, such that a rotation of the second arm device 36 is driven by a rotation of the first arm device 30. Further, the pivotable end 32 of the first arm device 30 is rotatably connected to a rear portion 40 of the slat 16, or at least configured therefor. Furthermore, a pivotable end 42 of the second arm device 36 is rotatably connected to a front portion 44 of the slat 16, or at least configured therefor. As a result, the first arm device 30 may at least indirectly drive the rotation of the second arm device 36. In case the slat 16 is rotatably connected to the first and second arm devices 30, 36, the first arm device 30 primarily drives the slat 16. Since the second arm device 36 is also rotatably connected to the slat 16, the second arm device 36 is extended based on the linkage between the first arm device 30 and the second arm device 36 provided by the slat 16. As a result, the extension of the second arm device 36 may be referred to as a passive extension, since the extension of the second arm device 36 is not actively driven by the second arm device 36 as such. Instead, the first arm device 30 is at least indirectly responsible for the rotation and extension of the second arm device 36. It is to be noted, that a movement of the slat 16 from the operation position to the retracted position will cause a reverse change in the rotation and extension of the second arm device 36.

[0077] Considering the system 18 in further detail, the system 18 comprises a first hinge support element 46 of the aircraft wing structure 14, a second hinge support element 48 of the aircraft wing structure 14, the first arm device 30, the second arm device 36 and the third arm device 38. The first arm device 30 is rotatably connected by an associated first connection junction 50 to the first hinge support element 46. The first arm device 30 comprises a second connection junction 52, which is configured to be or is rotatably connected to a rear portion 40 of the slat 16. Further, the first arm device 30 has a steady curved shape between the first connection junction 50 and the second connection junction 52. The first arm device 30 still further comprises a third connection junction 56 being arranged between the first and second connection junction 50, 52 of the first arm device 30. The third connection junction 56 of the first arm device 30 serves as a basis for a linkage between the first arm device 30 and the second arm device 36.

[0078] The second arm device 36 is linearly extendable and rotatably connected by an associated first connection junction 58 to the second hinge support element 48. Further, the second arm device 36 comprises a second connection junction 60, which is configured to be or is rotatably connected to a front portion 44 of the slat 16. The front 44 of the slat 16 is the portion of the slat 16, which borders upon the forward leading edge 24 of the slat 16. The second arm device 36 still further comprises a third connection junction 64 arranged between the first and the second connection junction 58, 60 of the second arm device 36. The third connection junction 64 of the second arm device 36 serves as the basis for linkage between the first arm device 30 and the second arm device 36.

[0079] The third arm device 38 is rotatably connected by an associated first connection junction 66 to the third connection junction 56 of the first arm device 30. Further, the third arm device 38 is rotatably connected by an associated second connection junction 68 to the third connection junction 64 of the second arm device 36. Due to its connections to the first and second arm device 30, 36, the third arm device 38 serves as a linkage between the first arm device 30 and the second arm device 36. Consequently, a rotation of the first arm device 30 about the first hinge support element 46 drives a corresponding rotation of the second arm device 36 about the second hinge support element 48. The first hinge support element 46 is arranged forward to the second hinge support element 48, such that a rotation of the first arm device 30 results in a smaller rotation of the second arm device 36.

[0080] In order to initiate a rotation of the first arm device 30, the system comprises a drive unit 70. The drive unit 70 preferably comprises a hydraulic and/or an electrical rotary actuator 72. The actuator 72 is preferably connected to the first arm device 30 via a further arm device 74. In particular, the drive unit 70 is configured to drive the first arm device 30 at least between a first pivot position, as exemplarily shown in FIG. 1, and a second pivot position, as exemplarily shown in FIG. 5. Instead of driving the first arm device 30, the drive unit 70 may be configured to drive the second arm device 36 and/or the third arm device 38. Due to the linkage between the first, second and third arm device 30, 36, 38, a respective movement and/or rotation may be provided.

[0081] In the first pivot position of the first arm device 30, as exemplarily shown in FIG. 1, the system 18 is configured to arrange the slat 16 in a retracted position fully arranged within the aircraft wing 2. As can be seen from FIG. 1, the slat 16, in particular its lower surface panel 22, does not form a part of the lower surface panel 8 of the aircraft wing 2. Accordingly, the slat 16 may have an arbitrary outer shape. Thus, the shape of the slat 16 may be formed, such that a higher lift coefficient may be provided, when the slat 16 is in its operation position, as it is exemplarily shown in FIG. 5.

[0082] In order to drive the slat 16 from the retracted position to the operation position, the aircraft wing 2 preferably comprises a bottom panel 76 at the lower surface panel 8. The bottom panel 76 is preferably rotatably connected to the (remaining) lower surface panel 8 of the aircraft wing 2. In order to move the slat 16 out of the aircraft wing 2, the bottom panel 76 opens a gap in the surface at the lower surface panel 8 of the aircraft wing, such that a lower opening 78 is provided. FIGS. 2 and 3 show, how the bottom panel 76 may be rotated, in order to provide the lower opening 78, through which the slat 16 may be moved downward and forward in order to reach the operation position.

[0083] Even though it is not shown in the figures, the system 18 may comprise a further drive unit being configured to move the bottom panel 76. The further drive unit may be controlled, such that the bottom panel 76 is moved to provide the lower opening 78 for the slat 16, if a movement of the slat 16 from the retracted position to the operation position, or vice versa, is initiated. At least if the slat 16 is in its retracted position, the further drive unit is controlled, such that the bottom panel 76 closes the lower opening 78, in order to provide a smooth lower surface profile of the aircraft wing 2.

[0084] FIGS. 1 to 5 show an alternative embodiment for driving the bottom panel 76. For this embodiment, the system 18 further comprises a fourth arm device 80, which is linked to one of the remaining arm devices 30, 36, 38 of the system 18. Preferably, the fourth arm device 80 is linked to the first arm device 30. Considering this embodiment in further detail, the first arm device 30 comprises a fourth connection junction 82, wherein the fourth arm device 80 is rotatably connected by an associated first connection junction 84 to the fourth connection junction 82 of the first arm device 30 and wherein the fourth arm device 80 is rotatably connected by an associated second connection junction 86 to the bottom panel 76. As a result, a rotation of the first arm device 30 will cause a rotation of the bottom panel 76 due to its linkage by the fourth arm device 80. Instead of rotating the bottom panel 76, the bottom panel 76 may alternatively be linearly shifted or moved in another way, such that the lower opening 78 is provided.

[0085] During the rotation of the first arm device 30 from its first pivot position to its second pivot position, the second arm device 36 is linearly extended, as it is shown in FIGS. 2 and 3. The extension of the second arm device 36 is forced by the first arm device 30, since the slat 16 provides a linkage between the pivotable ends 32, 42 of the first and second arm devices 30, 36, respectively. Therefore, the system 18 is configured to drive the slat 16 from the retracted position to the operation position along a trajectory, such that the forward leading edge 24 of the slat 16 is constantly forward to the rear leading edge 26 of the slat 16. Consequently, the slat is oriented in its retracted position, in its operation position and in any position therebetween, such that the forward leading edge 24 of the slat 16 is forward to the rear trailing edge 26 of the slat 16.

[0086] FIG. 4 shows the aircraft wing 2 as well as the system 18 in a schematic, perspective view, which corresponds to the cross-sectional view provided in FIG. 3. With regard to the second arm device 36, it can be seen, that the second arm device 36 comprises, in a preferred embodiment, a first shaft element 88 and a second shaft element 90. The first and second shaft elements 88, 90 are connected by a linear guide mechanism, which is preferably formed by the first and second shaft elements 88, 90 itself. In particular, the linear guide mechanism is formed as a parallel guide or a curved guide. The linear guide mechanism is configured to provide a translational shift between the first and second shaft elements 88, 90, such that the second arm device 36 is linearly extendable. It can further be taken from FIG. 4, that the extension of the second arm device 36 is passively driven by the first arm device 30, being linked to the second arm device 36, and in more detail to the second shaft element 90, via the slat 16. In order to provide this passive extension of the second arm device 36, the first shaft element 88 is rotatably connected by the associated first connection junction of the second arm device 36 to the second hinge support element 48. The first shaft element 88 further comprises the associated third connection junction 64 of the second arm device 36, such that the first shaft element 88 is linked via the third arm device 38 with the first arm device 30. The second shaft element 90 comprises the associated second connection junction 60 of the second arm device 36, in order to be rotatably connected to the front portion 44 of the slat 16.

[0087] FIG. 6 shows in a schematic, cross-sectional view a further embodiment of the aircraft wing 2 and/or the system 18. The bottom panel 76 is connected via an elastic element 92, in particular a spring, to the aircraft wing structure 14 or the drive unit 72, such that a tensile load is applied to the bottom panel 76 forcing the bottom panel 72 to close the lower opening 78. When driving the slat 16 from the retracted position to the operation position, one of the arm devices 30, 36, 38, in particular the second arm device 36, and/or the slat 16 pushes against the inside surface bottom panel 76 or a roller element 77 arranged on the inside surface of the bottom panel 76, such that the bottom panel 76 moves to open the lower surface 12 to provide the lower opening 78. Due to the tensile load applied to the bottom panel 76, the bottom panel 76 opens just as far as needed for the movement of the slat 16. In particular, the bottom panel 76 closes automatically as far as possible due to the spring tension load, in particular while the slat 16 is in its operation position, as exemplarily shown in FIG. 7. As a result, air drag resulting from moving the bottom panel 76 may be kept as low as possible.

[0088] According to a further exemplarily embodiment shown in the schematic, cross-sectional views of FIGS. 8 and 9, the system 18 is configured to lock the bottom panel 76, if the slat 16 is in its retracted position. In particular, the first arm device 30 links to a flange element 94 arranged at the bottom panel 76, resulting in a forced closure of the bottom panel 76, when the first arm device 30 reaches its first pivot position.

[0089] FIG. 10 schematically shows a top view of an aircraft 96 comprising the aircraft wing 2.

[0090] According to a further preferred embodiment of the invention, a method for driving the slat 16 of an aircraft 96 is provided. The method comprises the step a) of driving the slat 16 out of the lower opening 78 of the aircraft wing 2 in a downward and forward movement. Preferably, the forward leading edge 24 of the slat 16 is forward to a rear trailing edge 26 of the slat 16 during the aforementioned driving step a). A corresponding movement of the slat 16 can be recognized from the synopsis of the FIGS. 1 and 2, wherein the slat 16 is at least basically subject to a parallel movement out of the interior of the aircraft wing 2 through the lower opening 78. As a result, the bottom panel 76 has to be pivoted just about a small pivoting angle, which reduces a respective drag.

[0091] According to a further step b) of the method, the slat 16 is driven thereafter in an upward and forward movement in front of the aircraft wing 2. Preferably, the forward leading edge 24 of the slat 16 remains forward of the rear trailing edge 26 of the slat 16. A respective movement is apparent from the synopsis of the FIGS. 2, 3 and 5. As can be taken from the combination of FIGS. 2 and 3, the slat 16 is basically moved forward and upward at the same time. However, as can be taken from FIG. 3, and as a result of the curved shape of the first arm device 30, the rear trailing edge 26 of the slat 16 is subject to a larger upward movement than the forward leading edge 24 of the slat 16 during the movement step b). In particular, the angle of attack α between the airstream direction A and the chord line C of the slat 16 changes mainly during this step b). In other words, a larger decrease of the angle of attack α is performed during step b) than during the movement of step a).

[0092] The method further comprises the step c) of driving the slat 16 thereafter in an upward and backward movement. Preferably, the forward leading edge 24 of the slat 16 remains forward to the rear trailing edge 26 of the slat 16. A corresponding movement of the slat 16, at least basically, results from the curved shape of the first arm device 30, since its curved end section may be configured to encompass the forward leading edge surface panel 6 of the aircraft wing 2, such that the rear trailing edge 26 is driven to the upside of the aircraft wing 2 and further such that the rear trailing edge 26 is in overlap with the forward leading edge surface panel 6 of the aircraft wing 2. As a result, a gap 28 between the rear trailing edge 26 of the slat 16 and the surface of the aircraft wing 2 may be kept small, which increases the lift coefficient and enhances a flow, in particular a laminar flow.

[0093] While certain embodiments of the invention have been illustrated and described in detail in the drawings and foregoing description, such illustration and description are to be considered illustrative or exemplary and not restrictive. The claimed subject matter is not limited to the disclosed embodiments. Other variations to the disclosed embodiments can be understood and effected by those skilled in the art in practicing a claimed invention, from a study of the drawings, the disclosure, and the dependent claims.

[0094] In the claims, the word “comprising” does not exclude other elements or steps, and the indefinite article “a” or “an” does not exclude a plurality. For example, an arm device or other units may fulfil the functions of several items re-cited in the claims. The mere fact that certain measures are re-cited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to advantage. Any reference signs in the claims should not be construed as limiting the scope.