Wing leading edge device and wing having such a wing leading edge device

Abstract

A wing leading edge device (2, 42) is proposed, comprising a slat body (4, 42) having a front side (6) with a front skin (8) and a rear side (10) with a rear skin (12), and at least one drive device (14), the at least one drive device (14) having at least one projection (18, 20) and a slat guide rail (16), wherein the rear side (10) extends between an upper span edge (26) of the front skin (8) and a lower span edge (28) of the front skin (8), wherein the rear side (10) is defined by a continuously curved curved profile for receiving a fixed leading edge (32), wherein the at least one projection (18, 20) is at least partially arranged between the rear side (10) and the front side (6), and wherein the slat guide rail (16) is connected to the at least one projection (18, 20). The connection point to the slat body (4, 42) is moved further forward to improve load introduction and reduce the torque acting on the drive mechanism.

Description

Technical Field

[0001] The invention relates to a wing leading edge device, a wing with a fixed leading edge and the wing leading edge device, and an aircraft. Background Art

[0002] In order to increase the lift coefficient of commercial aircraft wings, high lift systems are known. These high lift systems may include trailing edge flaps and leading edge devices. During take-off and landing, they are usually activated, i.e. moved from a retracted position to an extended position. For this purpose, a drive mechanism is used, which is connected to the corresponding flow body and drive by appropriate joints, gears and other devices.

[0003] The leading edge slats usually include a front skin, a rear skin and a mechanical joint for coupling with the slat rail. The leading edge slats are designed to be arranged directly in front of the fixed leading edge of the wing, wherein the drive mechanism protrudes from the fixed leading edge toward the slats. Common embodiments include slat rails guided by track support rollers arranged in the fixed leading edge, wherein the slat rails protrude through the front spar of the fixed leading edge. For many load situations, the air load vector generated points further forward, and therefore has an offset with the engagement point on the leading edge slats. This offset results in the introduction of additional moments in the fixed leading edge structure.

[0004] EP3395679A1 shows a slat arranged on a wing, and a connection assembly for movably connecting the slat to a main wing so that the slat can be moved with a predetermined movement between a retracted position and at least one extended position. A front spar of a fixed leading edge of the wing, wherein an elongated guide of the connection assembly is completely arranged in an inner space between the front spar and the slat. Summary of the invention

[0005] An object of the present invention is to propose an alternative wing leading edge device which improves its coupling to the drive mechanism and reduces penetration through the structure fixing the leading edge.

[0006] This object is achieved by a wing leading edge device having the features according to an aspect of the invention. Advantageous embodiments and further developments can be gathered from the following description.

[0007] A wing leading edge device is proposed, comprising a slat body and at least one drive device, the slat body having a front side with a front skin and a rear side with a rear skin, the at least one drive device having at least one projection and a slat guide rail, wherein the rear side extends between an upper span edge of the front skin and a lower span edge of the front skin, wherein the rear side is defined by a continuously curved curved profile for receiving a fixed leading edge of the wing, wherein the at least one projection is at least partially arranged between the rear side and the front side, and wherein the slat guide rail is connected to the at least one projection.

[0008] The slat body may include an elongated shape extending along the span direction and include a specific curved profile. The curved profile is primarily determined by the desired aerodynamic properties. Preferably, the slat is strong enough for the intended purpose. Preferably, the slat body includes reinforcing elements, such as ribs and / or stringers arranged on the inner side of the front skin. In addition, some parts of the slat body may include a load introduction device that is mechanically suitable for reliable load transfer between the slat body and the drive mechanism.

[0009] The front skin is designed according to aerodynamic requirements. The front skin includes an upper edge and a lower edge, both of which extend in the span direction. The front skin extends between these edges in a substantially concave shape. At the rear position, that is, behind the inner side of the front skin, the rear side of the slat body is formed. The rear side is characterized by the following at least theoretical, surface-shaped boundary: the boundary is adapted to the outer shape of the fixed leading edge, and the wing leading edge device will be attached to the fixed leading edge. The rear side of the slat body is intended to be assembled to the fixed leading edge in a very tight manner in the retracted state. In some embodiments, the entire rear side includes a rear skin, which follows this theoretical surface-shaped shape. In some embodiments, this rear skin may include a cut-off portion or a recess. In a further embodiment, the rear skin may include a reduction portion along its entire span extension.

[0010] The coupling of the slat track to the at least one projection does not necessarily mean a direct connection. Additional connecting rods, plates or any other components arranged between the slat track and the at least one projection may also be used to couple the at least one projection and the slat track. Therefore, hereinafter, the term "coupling" is generally understood to mean a direct or indirect connection.

[0011] The gist of the invention is that at least one projection is provided at least partially between the rear side and the front side, i.e. between the rear side and the front skin. Therefore, the required joints and coupling means are substantially completely inside the slat body. This allows the reaction forces generated for the air load vector to be moved in the forward direction to form the significantly reduced offset mentioned above. Therefore, the additional moment acting on the fixed leading edge is also reduced. The slat rail does not need to be supported in the area behind the front spar of the fixed leading edge. Therefore, penetration through the front spar is eliminated, which in turn reduces the impact on the fixed leading edge design. In general, the design of the fixed leading edge has therefore been greatly improved.

[0012] It should also be understood that the wing leading edge device according to the present invention preferably comprises two above-mentioned drive devices for a single slat body to provide the desired movement of the entire slat body in the chord-wise direction.

[0013] In an advantageous embodiment, the front skin and the rear side enclose a hollow space, wherein the at least one projection is at least partially arranged in the hollow space. Thus, the at least one projection and the connection associated with the drive mechanism are provided in a further forward position, which results in a further improved coupling to the leading edge device and a further improved mechanical design for expected air load vector impacts.

[0014] In another advantageous embodiment, a hollow space is enclosed by the front skin and the rear skin, wherein the at least one projection is arranged completely in the hollow space. Thus, the final position for connection to the drive mechanism is as far forward as possible.

[0015] Advantageously, at least one drive device comprises a first projection, a second projection and a supporting link, wherein the supporting link is rotatably coupled with the second projection and the slat track. The supporting link therefore stabilizes the rotational position of the slat body. The arrangement of the first projection and the second projection at a distance from each other allows sizable moment to be transferred from the slat body to the slat track. In order to minimize the space required for this arrangement, the supporting link can be as small as possible.

[0016] The slat track may be rotatably coupled to the first protrusion.The first protrusion may be arranged in front of the second protrusion and the slat track may therefore be arranged as far forward as possible.

[0017] In a very advantageous embodiment, at least one projection is arranged on a reinforcing rib of the slat body. Thus, two functions are combined, namely a reinforcing function via the rib itself and a load introduction function via at least one projection incorporated into the rib.

[0018] Furthermore, the reinforcing rib may extend partially through the rear skin. In this embodiment, a balance is struck between compactness, available space, maintenance and bearing design. Although the rib and the first protrusion may be arranged completely within the space defined by the front skin and the rear side, it may be permitted for the rib to protrude slightly through the rear skin.

[0019] Advantageously, the slat body may include at least one cut-away portion through the rear skin for feeding the slat rail into the slat body. The cut-away portion may be as small as possible to allow the slat rail to be fed into the slat body, but may also leave sufficient clearance to take into account factors such as vibration, temperature deviations, loads and unloaded conditions. Furthermore, the cut-away portion may be designed to meet installation, assembly and disassembly requirements.

[0020] In the case of using a cut-away portion, it may be beneficial if the cut-away portion is arranged at a distance from at least one of the upper and lower edges. The cut-away portion can then extend over the inner portion of the rear skin only between the edges and, if necessary, up to one of the edges.

[0021] In another advantageous embodiment, the slat body can include a reduction of the rear skin, which extends in the spanwise direction substantially along the entire extension of the slat body, wherein at least one projection is arranged in the reduction. This design enables weight saving and simplifies installation, assembly and disassembly.

[0022] Preferably, the slat track comprises a curved track portion and a front leg, wherein the front leg is fixedly arranged at an angle relative to a tangent to the curved track portion at a connection point between the curved track portion and the front leg, and wherein the support link is rotatably connected to the front leg.

[0023] The invention also relates to a wing with a fixed leading edge and to a wing leading edge device according to the above description, wherein at least one drive device is connected to the fixed leading edge so that the slat guide is movably supported on the fixed leading edge so that the slat can be moved between a retracted position and an extended position, in which the rear skin is located directly in front of the front skin of the fixed leading edge and in the extended position the rear skin is located further forward of the fixed leading edge.

[0024] Advantageously, the fixed leading edge comprises a front spar, wherein the slat guide is supported by a plurality of guide support rollers, and wherein the guide support rollers are arranged between the front spar of the fixed leading edge and the front skin of the fixed leading edge. The rollers can be rotatably arranged on a reinforcing rib located in the fixed leading edge. The bearing for the rollers can therefore be arranged on a portion of the reinforcing rib that is arranged between the front skin of the fixed leading edge.

[0025] Furthermore, the drive device may be designed such that, at least in the retracted position of the slat, the vector of the air load on the slat body extends into the region between the first protrusion and the second protrusion. In the extended position, the vector of the air load may also extend into the region between the first protrusion and the second protrusion. The extended position may be a fully extended position or a less extended position. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Further features, advantages and potential applications of the invention are derived from the following description of the exemplary embodiments shown in the figures. In this regard, all described and / or illustrated features also constitute the subject matter of the invention individually and in any combination, regardless of their composition in the individual claims or their reference to other claims. In addition, identical or similar objects are identified in the figures by the same reference numerals.

[0027] Figure 1 A first exemplary embodiment of a leading edge device 2 is shown in a side view.

[0028] Figure 2 Typical air load vectors and resulting structural loads are shown in side view.

[0029] Figure 3 Another embodiment with a reduction along the span extension is shown in side view.

[0030] Figure 4 A roller guide for supporting a slat track is shown in side view.

[0031] Figure 5 The aircraft is shown in a three-dimensional view. DETAILED DESCRIPTION

[0032] Figure 1 A first embodiment of a wing leading edge device 2 is shown, which comprises a slat body 4 having a front side 6 with a front skin 8 and a rear side 10 with a rear skin 12. A drive device 14 is coupled to the slat body 4 and comprises a slat rail 16 and a first projection 18. In addition, a second projection 20 is arranged on the slat body 4 and coupled to a support link 22, which in turn is rotatably coupled to the slat rail 16 on a connection joint 24. The front skin 8 comprises an upper span edge 26 and a lower span edge 28. The front skin 8 extends between these two edges 26 and 28 and has a convex shape that protrudes outward in the forward direction. The rear side 10 extending between the edges 26 and 28 and at a distance from the front skin 8 constitutes the following boundary: the boundary is represented by the rear skin 12 and a dashed line 30 extending to the lower edge 28. The rear skin 12 comprises an upper rear skin edge 25 and a lower rear skin edge 27. Both rear skin edges 25 and 27 are attached to the front skin 8. Due to the design of the rear side 10, it is possible to move the slat body 4 close to the fixed leading edge 32 of the wing to which the device 2 is attached.

[0033] In this exemplary embodiment, the rear skin 12 comprises a cut-out portion 34 which is at a distance from both the upper edge 26 and the lower edge 28. The cut-out portion 34 enables the slat rail 16 to be guided into a hollow space 36 of the slat body 4.

[0034] Furthermore, in this exemplary embodiment, the first protrusion 18 and the second protrusion 20 are arranged on a rib 38 inside the slat body 4. The rib 38 can be realized in the form of a reinforcing rib, which is configured to support the external geometry of the slat body 4 at least under the design air load. By arranging the cut-out portion 34 into the rear skin 12, the rear side of the rib 38 can be easily accessible for connection with the slat rail 16 and the support link 22. Therefore, compared with a conventional leading edge device, the slat rail 16, the support link 22 and the protrusions 18 and 20 are arranged further forward so that the drive mechanism 14 is almost in the forwardmost position. This improves the transmission of air loads to the drive mechanism 14 and reduces the moment that needs to be compensated at the outer end of the slat rail 16. In addition, the rib 38 is used to support the slat rail 16 (see Figure 4 ) can be smoothly moved in the forward direction to be placed in front of the front spar with the fixed leading edge 32 (see Figure 4 ).

[0035] In this exemplary embodiment, the slat track 16 comprises a curved track portion 17 and a front leg 19, with a connection point 21 located between the curved track portion 17 and the front leg 19. The front leg 19 is arranged at an angle α to a tangent line 21 of the curved track portion 17 at the connection point 21. A support link 22 is rotatably connected to the front leg 19.

[0036] Figure 2 The resultant force inside the leading edge device 2 depending on the air load acting on the slat body 4 is shown. Two slightly different examples are shown, which are numbered I and II. Load case I represents an air load vector 40, whose direction extends directly through the first protrusion 18. In another load case II, the air load vector 40 is slightly offset compared to the load case I. Here, the vector extends through the position between the first protrusion 18 and the connecting joint 24. In the first condition I, basically only the first protrusion 18 needs to compensate the air load by a corresponding reaction force 41, and therefore the reaction force 41 can be basically the opposite force of the air load. However, in the second condition II, both the first protrusion 18 and the connecting joint 24 need to compensate the air load 40 by their own reaction forces 43a and 43b. However, in the common leading edge device, the air load vector 40 is offset in the forward direction, so that the reaction forces 43a and 43b are much larger.

[0037] exist Figure 34 shows a slightly modified slat body 42 in a wing leading edge device 45, which comprises a complete reduction 44 extending substantially along the entire span extension of the slat body 42. Here, the ribs 38 can protrude into the reduction 44 and the first and second projections 18, 20 can be easily accessed between the front skin 8 and the rear side 10. This exemplary embodiment has an advantageously low weight and still allows the slat body 42 to be positioned close to the fixed leading edge 32.

[0038] Figure 4 The figure shows possible rollers or roller guides 46 supporting the slat track 16. The roller guides 46 are rotatably supported and distributed in the fixed leading edge 32 to provide a single movement path for the slat track 16. Therefore, the slat track 16 can only move along a single movement path that depends on the shape of the slat track 16 and the position of the roller guides 46. All loads introduced into the drive mechanism 14 can be transferred to the fixed leading edge 32 through the roller guides 46.

[0039] Using common design concepts, the fixed leading edge 32 includes a reinforcement structure that may include a plurality of spars. The front spar 48 is arranged at a forward position at a distance from the actual leading edge. By moving the drive mechanism 14 and thus the roller guide 46 further forward than in a conventional leading edge device, the front spar 48 does not need to be passed through by the slat track 16. Therefore, the structural stability of the fixed leading edge 32 is not affected by any recess or cut-away portion required for the movability of the slat track 16.

[0040] at last, Figure 5 An aircraft 50 is shown having a wing 52 on which a wing leading edge device 2 is arranged.

[0041] In addition, it should be noted that "comprising" does not exclude other elements or steps, and "a" or "an" does not exclude a plurality. In addition, it should be noted that the features or steps described with reference to one of the above exemplary embodiments may also be used in combination with other features or steps of the other exemplary embodiments described above. The reference numerals in the claims should not be interpreted as limitations.

[0042] Reference numerals list

[0043] 2 Leading edge device

[0044] 4 slat body

[0045] 6 Front

[0046] 8 Front skin

[0047] 10 Rear

[0048] 12 Rear skin

[0049] 14 Drive device

[0050] 16 Slat rail

[0051] 17 Curved rail section

[0052] 18 first protrusion

[0053] 19 front legs

[0054] 20 Second protrusion

[0055] Connect the dots 21

[0056] 22 Support link

[0057] 23 Tangent

[0058] 24 Connector

[0059] 26 Upper wingspan edge

[0060] 28 Lower wing edge

[0061] 30 dotted line

[0062] 32 Fixed leading edge

[0063] 34 Cut off part

[0064] 36 Hollow Space

[0065] 38 Reinforcement ribs

[0066] 40 Air load vector

[0067] 41 Reaction force

[0068] 42 slat body

[0069] 43a, 43b reaction force

[0070] 44 Reduction

[0071] 45 Leading edge device

[0072] 46 Roller guide

[0073] 48 front wing spar

[0074] 50 Aircraft

[0075] 52 Wing

Claims

1. A wing leading edge device (2, 45), comprising a slat body (4, 42) having a front side (6) with a front skin (8) and a rear side (10) with a rear skin (12), and at least one drive device (14) having at least one protrusion (18, 20) and a slat guide rail (16), in, The rear side (10) extends between an upper span edge (26) of the front skin (8) and a lower span edge (28) of the front skin (8), wherein the rear side (10) is defined by a continuously curved curved profile for receiving a fixed leading edge (32) of a wing (52), wherein the at least one projection (18, 20) is at least partially arranged between the rear side (10) and the front side (6), wherein the slat guide rail (16) is connected to the at least one protrusion (18, 20), The at least one driving device (14) comprises a first protrusion (18), a second protrusion (20) and a supporting connecting rod (22). wherein one end of the support link (22) is rotatably connected to the second protrusion (20), and the other end of the support link (22) is rotatably connected to the slat guide rail (16), wherein the fixed leading edge (32) comprises a front spar (48), the slat guide rail (16) does not pass through the front spar (48), and The slat body (4, 42) comprises at least one cut-away portion (34) passing through the rear skin (12) for feeding the slat track (16) into the slat body (4, 42).

2. The wing leading edge device (2, 45) according to claim 1, in, The front skin (8) and the rear side (10) enclose a hollow space (36), wherein the at least one projection (18, 20) is at least partially arranged in the hollow space (36).

3. The wing leading edge device (2, 45) according to claim 2, in, The hollow space (36) is enclosed by the front skin (8) and the rear skin (12), and Therein, the at least one projection (18, 20) is arranged completely within the hollow space (36).

4. A wing leading edge device (2, 45) according to any one of claims 1 to 3, in, The slat rail (16) is rotatably coupled to the first protrusion (18).

5. A wing leading edge device (2, 45) according to any one of claims 1 to 3, in, The at least one protrusion (18) is arranged on a reinforcing rib (38) of the slat body (4, 42).

6. The wing leading edge device (2, 45) according to claim 5, in, The reinforcing rib (38) extends partially through the rear skin (12).

7. The wing leading edge device (2, 45) according to claim 1, in, The rear skin (12) includes an upper rear skin edge (25) and a lower rear skin edge (27) attached to the front skin (8), and The cut-away portion (34) is arranged at a distance from at least one of the upper rear skin edge (25) and the lower rear skin edge (27).

8. A wing leading edge device (2, 45) according to any one of claims 1 to 3, in, The slat body (4, 42) comprises a tapered portion (44) of the rear skin (12) extending in spanwise direction substantially along the entire extension of the slat body (4, 42), wherein the at least one projection (18, 20) is arranged in the tapered portion (44).

9. A wing leading edge device (2, 45) according to any one of claims 1 to 3, in, The slat track (16) comprises a curved track portion (17) and a front leg (19), wherein the front leg (19) is fixedly arranged at an angle (α) relative to a tangent (23) to the curved track portion (17) at a connection point (21) between the curved track portion (17) and the front leg (19), and Wherein, the support link (22) is rotatably connected to the front leg (19).

10. A wing (52) having a fixed leading edge (32) and a wing leading edge device (2, 45) according to any one of claims 1 to 9, in, The at least one drive device (14) is coupled to the fixed leading edge (32) such that the slat track (16) is movably supported on the fixed leading edge (32) in a manner that enables the slat body (4, 42) to move between a retracted position in which the rear skin (12) is located directly in front of a front skin of the fixed leading edge (32) and an extended position in which the rear skin (12) is located further forward of the fixed leading edge (32).

11. The wing (52) according to claim 10, in, The fixed leading edge (32) comprises a front spar (48), The slat guide rail (16) is supported by a plurality of roller guides (46), and Wherein, the roller guide (46) is arranged between the front spar (48) of the fixed leading edge and the front skin of the fixed leading edge.

12. The wing (52) according to claim 10 or 11, in, The drive device (14) is designed such that, at least in the retracted position of the slat body (4, 42), the air load vector (40) on the slat body (4, 42) extends into the area between the first projection (18) and the second projection (20).

13. An aircraft (50) having at least one wing (52) according to any one of claims 10 to 12.

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