Flap systems, wings and aircraft

Abstract

A flap system includes a leading-edge flap, an actuator, first, second, and third fixed links, first and second connecting links, and an auxiliary link. The first and third fixed links each include a first and third support joint rotatably supported at first and third structural fixing points, respectively. The first fixed link includes a first connecting joint connected to one end of the first connecting link (the other end of which is connected to a first flap joint). The second fixed link includes a second connecting joint rotatably connected to the central region of the first connecting link. The third fixed link includes a third connecting joint rotatably connected to one end of the second connecting link (the other end of which is connected to a second flap joint). The second connecting link and the first fixed link are connected at their respective ends by an auxiliary link. The fixed, connecting, and auxiliary links are arranged to actively deploy the leading-edge flap from a retracted position to an extended position. This application also provides a wing and an aircraft including this flap system.

Description

Technical Field

[0001] The present invention relates to a system for driving flap arrangements between a retracted position and an extended position, a wing having such a system, and an aircraft. Background Technology

[0002] In commercial aircraft, so-called high-lift systems are typically located on the wings, allowing for an increase in the wing's lift-generating area and camber. These high-lift systems primarily include trailing-edge flap arrangements and leading-edge flap arrangements. For example, a leading-edge flap arrangement includes flaps extending from a recess on the underside of the wing to a position on the upper side of the wing. For this type of so-called Kruger flap, there are many different actuation mechanisms.

[0003] Kruger flaps are typically located under the wing, with the trailing edge pointing forward and the leading edge pointing backward. During deployment, the flaps generally follow a rotational motion to reach a position in front of the wing's leading edge and create a gap therebetween, with the leading edge pointing in the direction of flight and the trailing edge pointing backward.

[0004] DE 102011018906 A1 exemplarily illustrates a leading-edge flap system with a Kruger flap. Here, an additional retaining element is attached to the trailing edge of the flap to affect the clearance between the flap and the leading edge of the wing.

[0005] EP 2509859 B1 illustrates a high-lift system that may also include a Kruger flap designed to shape the resulting gap between the flap and the leading edge of the wing into a strictly convergent shape. Summary of the Invention

[0006] The conventional kinematics used to extend leading-edge slats in the form of Kruger flaps typically provides a strict motion for the leading-edge flap attached to a lever that rotates about an axis of rotation. Therefore, the angle between the flap's chord axis and the wing's chord axis is substantially proportional to the position of the lever. However, it can be advantageous to provide different motions to optimize the clearance between the leading-edge flap and the wing's leading edge, as well as the airflow over the flap and the wing.

[0007] Therefore, the object of the present invention is to provide an improved flap system for providing movement of the leading edge flap, which improves flow in the flap region, while the system should be as simple as possible.

[0008] This objective is achieved by the flap system according to the invention. Advantageous embodiments and further improvements can be obtained from the following description.

[0009] A flap system for driving a leading-edge flap between a retracted position and an extended position is proposed. The system includes: a leading-edge flap, an actuator, a first fixed link, a second fixed link, a third fixed link, a first connecting link, a second connecting link, and an auxiliary link. The first fixed link includes a first support joint for rotatably supporting the first fixed link on a first structural fixing point. The second fixed link includes a second support joint for rotatably supporting the second fixed link on a second structural fixing point. The third fixed link includes a third support joint for rotatably supporting the third fixed link on a third structural fixing point. The first fixed link includes a first support joint connected to the first fixed link. A first connecting joint is connected to one end of a connecting rod, the first connecting rod being connected to a first flap connector at its other end; a second fixed connecting rod includes a second connecting joint rotatably connected to the central region of the first connecting rod; a third fixed connecting rod includes a third connecting joint rotatably connected to one end of the second connecting rod, the second connecting rod being connected to a second flap connector at its other end; the actuator, the second connecting rod, and the first fixed connecting rod are each connected at their respective ends via auxiliary connecting rods; and the fixed connecting rod, the connecting rod, and the auxiliary connecting rod are arranged to actively place the leading edge slat from a retracted position to an extended position.

[0010] Using the flap system according to the invention, certain aerodynamic flap positions can be reached, resulting in higher lift performance. A key advantage is that the trailing edge of the Kruger flap remains below the wing leading edge until a midpoint with a deployment angle of approximately 117° measured between the local wing chord and the leading-edge flap chord. The gap between the trailing edge of the flap and the wing leading edge can also be 2% or less of the local wing chord. This prevents airflow separation on the main wing during Kruger flap deployment. In subsequent movements, an extended position can be reached, which may include an angle of approximately 130° between the local flap chord and the local wing chord, while maintaining the size of the gap. In summary, the flap system according to the invention enables more complex movements of the leading-edge flap that optimize flow at least in the leading-edge region. The direct link between angle adjustment and flap deployment is eliminated.

[0011] The arrangement of the links connecting the three structural anchor points will allow the angle between the flap and the wing chord to change until a certain state is reached. After this, the flap angle can remain essentially constant, or it can increase only slightly. This means that the desired flap deployment angle can be achieved almost at the midpoint before the flap is fully deployed and while still partially below the wing chord. Subsequently, the flap can provide essentially translational motion, i.e., motion during the subsequent essentially parallel motion.

[0012] Leading-edge flaps can be elongated and have a flowing body with leading and trailing edges. They can bend in a manner similar to a standard Kruger flap or another flow-influencing control surface of an aircraft. Main flaps are leading-edge flaps designed to move relative to the wing's leading edge. In the retracted state, the flaps are arranged in a recess on the underside of the wing when the flap system is installed in the wing. The movements mentioned in this application refer to deployment movements from said recess to a position ahead of the wing's leading edge.

[0013] The flap system according to the invention is based on the arrangement of six links in the first embodiment. Three fixed links are rotatably supported on three separate structural anchor points. Two connecting links are rotatably supported on two separate flap joints, which are arranged at a distance from each other on the leading edge flap. The spatial position of the flap joints, and thus the spatial position of the flap, is determined by the interconnection of the fixed links and connecting links (this connection also includes the use of auxiliary links). To drive the arrangement of the links, an actuator can be coupled to one of the fixed links. These components will be described in more detail below.

[0014] The actuator can be a rotary actuator, which is exemplarily directly connected to one of the fixed links in a fixed linkage. When mounted on a wing, the actuator can also be connected to a structural anchor point. Through the rotary actuator, the corresponding fixed link rotates about the corresponding structural anchor point, thereby moving all links directly or indirectly connected to it.

[0015] The first and second fixed links each include an end rotatably supported on a separate structural fixing point and an opposite end rotatably connected to the first connecting link. By rotating the first and second fixed links about their respective support joints (which, in the installed state, are connected to the structural fixing points), the first connecting link is forced to perform a movement determined by the positions of the first and second structural fixing points, the lengths of the first and second fixed links, and the connection position on the first connecting link.

[0016] Exemplarily, the first connecting link may be divided into two halves along its main extension. At the outer end of one half, the first connecting link is connected to a first flap connector. At the other half, it may be connected to a first fixed link and a second fixed link. Preferably, the first fixed link is connected to the outer end of the first connecting link, while the second fixed link is connected to a position on the first connecting link offset towards the center of the first connecting link. In the retracted position, the first and second fixed links may be arranged substantially parallel to each other, and the first fixed link may include a longer length than the second fixed link. Therefore, in the retracted position, the first connecting link is significantly inclined relative to the first and second fixed links. As a result, in the first part of the deployment process, the first connecting link will maintain its orientation, and the outer end of the first connecting link will thus move along a substantially circular path.

[0017] Based on the length relationship between the first fixed link and the second fixed link, as well as the positions of the first structural fixing point and the second structural fixing point, the orientation of the first connecting link will change along the unfolding process, so that after the first part of the unfolding process, the radius of the movement path of the outer end of the first connecting link becomes smaller and smaller.

[0018] Simultaneously, the third fixed link and the auxiliary link force the second connecting link to perform a certain movement. While the auxiliary link moves directly according to the first fixed link, the auxiliary link and the third fixed link determine the orientation of the second connecting link. Preferably, the second flap joint performs a movement similar to the first flap joint, i.e., a rotational movement with a decreasing radius after the first part is deployed. Therefore, the flap system according to the invention can be adjusted such that even when the trailing edge of the flap is below the wing chord to which the flap system can be attached, the leading edge of the flap is in a relatively far forward position. The leading edge flap will preferably take an angle of approximately 117° relative to the wing chord, while the trailing edge of the flap remains below the chord, followed by a substantially parallel or translational movement. This can result in an angle of approximately 130°. Thus, a certain gap is maintained between the flap and the wing leading edge.

[0019] In a preferred embodiment, the first fixed link has a longer length than the second fixed link. This allows the flap system according to the invention to provide a specific path of motion for the first flap connector as described above. The difference in length will cause a significant change in the orientation of the first connecting link in a specific deployment state.

[0020] Preferably, in the retracted position, the first fixed link and the second fixed link form an angle of less than 10°. Therefore, in this position or the deployed state, the first and second fixed links are arranged substantially parallel to each other. This causes the movement of the first connecting link to follow a generally circular path until the orientation of the first connecting link changes more sharply, causing the first flap joint to move with a decreasing radius. Therefore, the movement of the first flap joint has a helical tendency.

[0021] In the retracted position, the first connecting link and the first fixed link form an angle ranging from 25° to 45°. The first connecting link is connected to the end of the first fixed link opposite to the first structural fixing point. To achieve the above movement, it is preferable that when the flap is retracted, the ends of the first connecting link and the first fixed link are in their most extended positions. Therefore, the first connecting link is slightly oriented forward. During deployment, depending on the size of the second fixed link, the angle formed by the first fixed link and the first connecting link can be substantially the same in the fully extended position.

[0022] Preferably, the length of the third fixed link is at most half the length of the first fixed link. Due to the preferred forward position of the third fixed link, the end opposite to the third support joint only requires a relatively small radius of motion. Therefore, a smaller length is required. In this respect, it should be noted that the second connecting link and the auxiliary link may include lengths comparable to the length of the third fixed link, particularly at most half the length of the first fixed link.

[0023] Preferably, the fixed link, the connecting link, and the auxiliary link are arranged to: actively position the leading-edge flap from a retracted position to an intermediate position, in which the chord axis of the flap is adjusted to a desired angle; and to subsequently provide translational movement along the chord axis of the flap, while the orientation of the chord axis remains substantially constant. Therefore, all links used in the flap system are designed in a manner that enables this behavior. The orientation of the chord axis should therefore remain constant. Since the kinematic chain depends on rotational motion, it is sufficient to allow the orientation of the flap's chord axis to vary within ±2°. Thus, the flap, as described above, will be moved to a forward position where the chord has taken the desired angle just before reaching the chord axis of the wing. Afterward, the flap can move substantially translationally along the chord axis, with a certain gap between the wing leading edge and the leading-edge flap.

[0024] In an advantageous embodiment, the leading-edge flap includes a body portion and a nose portion, wherein the system further includes a third connecting link, a second auxiliary link, and a fourth connecting link, wherein the second connecting link is connected at one end to the third connecting link, wherein the third connecting link is connected to the second auxiliary link at the opposite end, wherein the central region of the second auxiliary link is rotatably supported on the first flap connector and is connected to the third connecting link at one end and to the fourth connecting link at the opposite end, and wherein the flap nose is connected to the fourth connecting link and the first flap connector. Thus, the leading-edge flap is divided into two parts that are movable relative to each other. They can be connected, exemplarily, by a hinge. This allows the flap to be easily stored on the underside of the wing, as the flap nose can be folded toward the flap body. For deploying the flap nose, a set of the third connecting link, the fourth connecting link, and the second auxiliary link is provided. A third connecting link transmits motion from the first connecting link to a second auxiliary link, which is preferably designed as a rocker arm. Therefore, when the third connecting link is pushed toward the first flap connector, the nose portion of the flap is pulled toward the first flap connector. This causes the flap to compress / fold in the retracted position. Therefore, the third connecting link is sized such that the distance between the attachment point of the third connecting link and the corresponding end of the nose portion of the third connecting link exceeds the distance to the first flap connector. During the extension movement, the third connecting link is pulled toward and beyond the second flap connector, causing the second auxiliary link to rotate to push the nose portion outward.

[0025] Furthermore, a single actuator can be used exclusively. Therefore, the advantages of the flap system can be achieved by moving only one link in the linkage, without the need for a second actuator to, for example, change the angle or translational position of the flap relative to the wing to which the flap system is mounted. The flap system according to the invention is simple yet effectively provides the desired movement of the flap.

[0026] Preferably, the fixed link, the connecting link, and the auxiliary link are arranged to: actively position the leading-edge slat from a retracted position to an intermediate position, in which the flap's chord axis is adjusted to a desired angle; and to subsequently provide translational movement along the flap's chord axis while the orientation of the chord axis remains substantially constant or slightly increased (e.g., by approximately 10° to 15°). Therefore, all links used in the flap system are designed in a manner that enables this behavior. Thus, the flap, as described above, is moved to a forward position where the local flap chord has already taken the desired angle just before reaching the wing's local chord axis. The flap can then be translated substantially along the chord axis to a fully extended position with a gap between the wing leading edge and the leading-edge flap.

[0027] As further described below, the specific angle in the intermediate position can be approximately 117°. In the extended position, this angle can be approximately 130°. However, depending on the aircraft's design, these angles can vary slightly (e.g., approximately + / - 2°).

[0028] The present invention further relates to a wing having a leading edge region and a trailing edge region and at least one flap system according to the above description.

[0029] Advantageously, the system is positioned in the leading edge region.

[0030] Preferably, the flap system is designed to move the flap below the wing leading edge until an angle of 117° is formed between the partial flap chord and the partial wing chord. This prevents airflow separation on the upper side of the wing. The position of the flap directly below the wing leading edge is considered the upper and further intermediate positions mentioned below.

[0031] As it extends from the intermediate position to the extended position, the partial flap chord reaches an exemplary angle of 130° relative to the partial wing chord. The flap then moves along the wing leading edge in a substantially translational motion while maintaining clearance.

[0032] The flap system is further designed to limit the clearance between the trailing edge of the flap and the leading edge of the wing to 2% of the local wing chord. This harmonizes the airflow from the flap to the upper side of the wing. The clearance between the trailing edge of the flap and the leading edge of the wing should not exceed 2% of the local wing chord. This prevents airflow separation on the wing during flap deployment. This can include an intermediate position. And, this can include an extended position.

[0033] Finally, the present invention relates to an aircraft having at least one such wing. Attached Figure Description

[0034] Other features, advantages, and potential applications of the invention will be derived from the following description of exemplary embodiments shown in the accompanying drawings. In this regard, all features described and / or illustrated also individually and in any combination form the purpose of the invention, regardless of their composition in the independent claims or their reference to other claims. Furthermore, in the drawings, identical or similar objects are identified by the same reference numerals.

[0035] Figures 1 to 7 A first exemplary embodiment of the flap system according to the present invention is shown in different views.

[0036] Figures 8 to 12 A second exemplary embodiment of the flap system according to the invention is shown in a different view.

[0037] Figure 13 An aircraft having a wing including at least one flap system according to the invention is shown. Detailed Implementation

[0038] Figure 1 A flap system 2 is shown mounted in the leading edge region 4 of wing 6. The flap system 2 includes a first fixed link 8 rotatably or rotatably mounted on a first structural anchor point 10. For example, the inner end 12 of the first fixed link 8 includes a first support joint 14 connected to the first structural anchor point 10 of wing 6. The first fixed link 8 further includes an outer end 16 opposite to the inner end 12. The term "outer end" should be understood as the end outside the profile of wing 6 in its extended position. Figure 1 The retracted position is shown in the diagram. Here, the first fixed link 8 extends further inward from the leading edge region 4 along a generally horizontal axis.

[0039] The flap system 2 further includes a second fixing link 18, which is rotatably or rotatably mounted on a second structural fixing point 20. For this purpose, the second fixing link 18 includes a second support joint 22. In the retracted position, the second fixing link 18 extends further inward from the leading edge region 4. In this position, the first fixing link 8 and the second fixing link 18 exemplarily form an angle of approximately 10°, which can also vary to 10°–15°. The first structural fixing point 10 is located slightly in front of and above the second structural fixing point 20. The length of the second fixing link 18 is less than the length of the first fixing link 8.

[0040] The flap system 2 further includes a first connecting link 24, which is connected at one end 26 to the end 16 of the first fixed link 8 and at the opposite end 30 to the first flap connector 28. The first connecting link 24 further includes an intermediate connector 32, which is then connected at the end opposite to the first support connector 20 to the second fixed link 18.

[0041] When the first fixed link 8 and the second fixed link 18 are moved, the first connecting link 24 is forced to move. This determines the movement of the first flap joint 30. Due to its orientation in the retracted position and the relationship between the first fixed link 8 and the second fixed link 18, the first flap joint 30 will rotate, and the radius of rotation will decrease from a certain deployment stage.

[0042] Furthermore, the flap system 2 includes a third fixed link 34, which is rotatably or pivotally supported on a third structural fixing point 36 by means of a third support joint 38. The end 40 opposite to the third support joint 38 is connected to a second connecting link 42, which in turn is connected to a second flap joint 44 at its end 46. An intermediate joint 50 is positioned between the ends 40 and 44 of the second connecting link 42, to which an auxiliary link 48 is connected. The opposite end of the auxiliary link 48 is connected to a first fixed link 8 at an auxiliary link joint 52, which is positioned between the first support joint 14 and the outer end 16. Therefore, the second connecting link 42 begins to move due to its connection with the third fixed link 34. Relative to the intermediate joint 50, the second connecting link 42 acts in a rocker-like manner, causing the second flap joint 46 to follow the rotational movement caused by the third fixed link 34. In addition, the intermediate link 50 moves via the action of the first fixed link 8. The third fixed link 34, the second connecting link 42, and the auxiliary link 48 have approximately the same order of length. However, due to the compact arrangement of these three links, the auxiliary link 48 has a curved shape. Additionally, the third fixed link 34 has an L-shaped or J-shaped form.

[0043] The deployment of flap joints 30 and 46 causes movement of the leading-edge flap 54, which carries flap joints 30 and 46. As described above, in Figure 1 The image shows the retracted position of flap 54. Here, flap 54 is positioned on the underside 56 of the wing, within recess 58. The leading edge 60 of flap 54 is in the rearward position, while the trailing edge 62 is in the forward position. Flaps 54 close recess 58 to create a harmonic outer surface.

[0044] exist Figures 2 to 4 The image shows other deployment phases of flap 54. Figure 2 Corresponding to Figure 4 The diagram also shows details between the trailing edge 62 and the leading edge 64 of wing 6. Here, the trailing edge 62 of flap 54 creates a gap 66, which should not exceed 2% of the local wing chord. Here, flap 54 is in the extended position.

[0045] exist Figure 3 The image shows the flap 54 in its intermediate position. Here, the partial flap chord 68 and the partial wing chord 70 form an angle α of approximately 117°, with the trailing edge 62 of the flap 54 directly below the wing chord 70. The flap 54 then provides a substantially parallel motion, changing the angle α only slightly to approximately 130°.

[0046] Figure 5 The arrangement of the flap system 2 is shown in a three-dimensional view. Here, it is evident that the first connecting link 24 and the auxiliary link 48 are the only components designed as a single unit. Since links 8, 18, 24, 34, 42, and 48 cross each other during deployment, the remaining links 8, 18, and 34 are arranged in pairs and symmetrically. Therefore, the first fixed link 8 is made of two first fixed sub-links 8a and 8b. The second fixed link 18 is implemented as two second fixed sub-links 18a and 18b. The same applies to the second connecting link 42, which includes two sub-links 42a and 42b. These are also... Figure 6 It is shown from another perspective.

[0047] Figures 7 to 12 A modified flap system 72 is shown, which includes additional components. These components include flaps 73 in different designs, taking the form of a main body portion 74 and a nose portion 76. A second connecting link 42 is additionally connected to a third connecting link 78, which extends from the second connecting link 42 to a second auxiliary link 80, which is rotatably supported about a central joint 82 on a first flap joint bracket 84. The two ends 86 and 88 of the second auxiliary link 80 rotate about the joint 82. A fourth connecting link 90 is connected to the second auxiliary link 80 and attached to a nose joint 92 arranged on the nose portion 76. Thus, the second auxiliary link 80 is forced to move by the third connecting link 78, thereby pulling or pushing the nose portion 76 outward.

[0048] exist Figure 7 In the middle, the flap system 72 is in the retracted position, with the nose portion 76 in a compact folded form. Figure 8 In the middle, the flap is slightly extended, in which the third connecting link 78 is pulled to the second connecting link 42, so that the fourth connecting link 90 is pushed outward.

[0049] exist Figure 9In the middle position, the flaps extend to an expected angle of approximately 117°, with flap 73 directly below the wing chord.

[0050] exist Figure 10 The image shows flap 73 after a subsequent substantially parallel movement, where flap 73 reaches an angle of approximately 130°. This is consistent with the description of the first exemplary embodiment. Figure 3 and Figure 4 The diagrams in the figures are quite similar. The positions shown in these figures are the extended positions.

[0051] Going further, Figure 11 and Figure 12 The flap system 72 is shown in a three-dimensional view. Here, the fourth connecting link and the second auxiliary link are shown as a double link. The same applies to the third connecting link 78.

[0052] at last, Figure 13 An aircraft 94 with two wings 96 is shown, to which flap system 2 or 72 can be mounted at the leading edge region 4.

[0053] Furthermore, it should be noted that "comprising" does not exclude other elements or steps, and "a" or "an" does not exclude a plurality. Additionally, it should be noted that features or steps described with reference to one of the exemplary embodiments described above may also be used in combination with other features or steps of the other exemplary embodiments described above. Reference numerals in the claims should not be construed as limiting.

Claims

1. A flap system (2, 72) for actuating a leading-edge flap between a retracted position and an extended position, the system comprising: -Leading edge flap (54, 73), -Actuator, -First fixed link (8), -Second fixed link (18), -Third fixed link (34), -First connecting link (24), -Second connecting rod (42), and -Auxiliary link (48), The first fixed link (8) includes a first support joint (14) for rotatably supporting the first fixed link (8) on the first structural fixing point (10). The second fixed link (18) includes a second support joint (22) for rotatably supporting the second fixed link (18) on the second structural fixing point (20). The third fixed link (34) includes a third support joint (38) for rotatably supporting the third fixed link (34) on a third structural fixing point. The first fixed link (8) includes a first connecting joint that connects to one end of the first connecting link (24), and the first connecting link connects to a first flap joint (28) at the other end. The second fixed link (18) includes a second connecting joint that is rotatably connected to the central region of the first connecting link (24). The third fixed link (34) includes a third connecting joint that is rotatably connected to one end of the second connecting link (42), and the second connecting link is connected to the second flap joint (44) at the other end. The second connecting rod (42) and the first fixed connecting rod (8) are connected at their respective ends by an auxiliary connecting rod (48), and The fixed link (8, 18, 34), the connecting link (24, 42), and the auxiliary link (48) are arranged to actively place the leading edge flap (54, 73) from the retracted position to the extended position.

2. The system (2, 72) as described in claim 1, in, The first fixed link (8) has a longer length than the second fixed link (18).

3. The system (2, 72) as described in claim 1 or 2, in, In the retracted position, the first fixed link (8) and the second fixed link (18) form an angle of less than 10°.

4. The system (2, 72) as described in any of the preceding claims, in, In the retracted position, the first connecting link (24) and the first fixed link (8) form an angle ranging from 25° to 45°.

5. The system (2, 72) as described in any of the preceding claims, in, The length of the third fixed link (34) is at most half the length of the first fixed link (8).

6. The system (2, 72) as described in any of the preceding claims, in, The fixed link (8, 18, 34), the connecting link (24, 42), and the auxiliary link (48) are arranged to: actively place the leading edge flap (54, 73) from the retracted position to the intermediate position, in which the chord axis of the flap (54, 73) is adjusted to the desired angle; And it is used to subsequently provide translational motion along the chord axis of the flaps (54, 73), while the orientation of the chord axis remains substantially constant.

7. The system (2, 72) as described in any of the preceding claims, in, The leading edge flaps (54, 73) include a main body portion (74) and a nose portion (76). It further includes a third connecting link (78), a second auxiliary link (80), and a fourth connecting link (90). The second connecting rod (42) is connected to the end of the third connecting rod (78), and the third connecting rod (78) is connected to the second auxiliary connecting rod (80) at the opposite end. The second auxiliary link (80) is rotatably supported on the first flap joint (28) at its central region, and is connected to the third connecting link (78) at one end and to the fourth connecting link (90) at the opposite end. The flap nose is connected to the fourth connecting rod (90) and the first flap connector (28).

8. The system (2, 72) as described in any of the preceding claims, in, Exclusively use a single actuator.

9. A wing (6) having a leading edge region (4) and a trailing edge region and at least one system (2, 72) as claimed in any one of claims 1 to 8 mounted in the wing (6).

10. The wing (6) as claimed in claim 9, wherein, The system (2, 72) is arranged in the leading edge region (4).

11. The wing (6) as claimed in claim 9 or 10, wherein, The system (2, 72) is designed to move the flaps (54, 73) below the leading edge (64) of the wing until an angle of 117° is formed between the partial flap chord (68) and the partial wing chord (70).

12. The wing (6) as claimed in any one of claims 9 to 11, wherein, The flap system (2, 72) is further designed to limit the gap (66) between the trailing edge (62) of the flap (54, 73) and the leading edge (64) of the wing (6) to 2% of the partial wing chord (70).

13. An aircraft having at least one wing (6) as claimed in any one of claims 9 to 12.

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