FLOW BODY FOR AN AIRCRAFT HAVING A SOLID TRAILING-EDGE COMPONENT

Abstract

A flow body for an aircraft, in particular for a wing leading edge device, is proposed, the flow body having a curved front skin having a leading edge and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is designed for providing a flush transition between the front skin and at least one of the two spanwise flow surfaces.

Claims

1-15. (canceled)

16. A flow body for a wing leading edge device of an aircraft, the flow body comprising: a curved front skin having a leading edge, and at least one trailing-edge component coupled with at least one spanwise edge of the front skin, wherein the trailing-edge component comprises a constant cross-sectional profile that tapers in a chordwise direction to form two spanwise flow surfaces that end in a trailing edge, and wherein the trailing-edge component is configured to provide a flush transition between the front skin and at least one of the two spanwise flow surfaces.

17. The flow body according to claim 16, wherein the trailing-edge component comprises at least one recessed spanwise receiving surface for receiving a spanwise edge region of the front skin, wherein the at least one receiving surface is delimited by a step facing the trailing edge, and wherein the step is configured to provide the flush transition between the front skin and the trailing-edge component.

18. The flow body according to claim 17, wherein the front skin is attached to the at least one receiving surface.

19. The flow body according to claim 16, wherein the cross-sectional profile of the trailing-edge component comprises at least one leg that extends away from the trailing edge to receive the front skin.

20. The flow body according to claim 19, wherein the flow body encloses a hollow space, wherein the trailing-edge component comprises two legs, which provide an open intermediate space, and wherein the hollow space extends into the intermediate space.

21. The flow body according to claim 20, wherein the flow body comprises the hollow space, in which at least one spar extends along a spanwise direction, wherein a rear air chamber is created rearward of the at least one spar, which rear air chamber extends from the at least one spar to a junction of the two legs.

22. The flow body according to claim 21, wherein a forward air chamber is created forward of the at least one spar, and wherein the rear air chamber and the forward air chamber are in a fluid communication.

23. The flow body according to claim 16, further comprising a back skin arranged at a distance to the front skin, wherein a spanwise edge of the back skin is arranged on the trailing-edge component.

24. The flow body according to claim 21, further comprising a back skin arranged at a distance to the front skin, wherein a spanwise edge of the back skin is arranged on the trailing-edge component, wherein the back skin is attached to the at least one spar, and wherein the rear air chamber is additionally delimited by the back skin.

25. The flow body according to claim 16, wherein the flow body is a leading-edge slat and wherein the trailing-edge component provides a trailing edge of the slat.

26. The flow body according to claim 16, wherein the trailing-edge component is an extruded part.

27. A wing having a fixed wing body and a wing leading edge device having a flow body according to claim 16.

28. The wing according to claim 27, further comprising an anti- or de-icing device providing air at an elevated temperature, which is in fluid communication with a hollow space of the flow body.

29. An aircraft having wings according to claim 27.

30. An aircraft having at least one flow body according to claim 16.

31. The aircraft of claim 30, wherein the flow body is a part of a wing leading edge device arranged on a fixed wing body of a wing.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0036] Other characteristics, advantages and potential applications of the present invention result from the following description of the exemplary embodiments illustrated in the figures. In this respect, all described and/or graphically illustrated characteristics also form the object of the invention individually and in arbitrary combination regardless of their composition in the individual claims or their references to other claims. Furthermore, identical or similar objects are identified by the same reference symbols in the figures.

[0037] FIG. 1 shows a first exemplary embodiment of a flow body.

[0038] FIG. 1A shows an enlarged portion A from FIG. 1.

[0039] FIG. 2 shows a second exemplary embodiment of a flow body.

[0040] FIG. 3 shows an aircraft having at least one flow body.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0041] FIG. 1 shows a sectional view of a flow body 2 for an aircraft, which is exemplarily realized in the form of a leading-edge slat. The flow body 2 comprises a curved front skin 4 having a leading edge 6 in at least one flow condition. The front skin 4 is curved to form an aerodynamic surface with a predetermined flow characteristic. Opposite to the leading edge 6, a trailing edge 8 is positioned. Exemplarily, a spar 10 extends between a top section 12 and a bottom section 14 of the flow body 2, on which the front skin 4 rests. At a side facing away from the leading edge 6, a back skin 16 is arranged, which is attached to a rear side of the spar 10 and extends towards the trailing edge 8.

[0042] The flow body 2 comprises a trailing-edge component 18, which comprises the trailing edge 8. It is an extruded or machined and solid component. For example, the trailing-edge component 18 is made from aluminum in an extrusion process.

[0043] The front skin 4 comprises a first spanwise edge 20, which constitutes an upper rear delimitation of the front skin 4. For receiving a first edge region 22, which comprises the first spanwise edge 20, the trailing-edge component 18 comprises a first recessed receiving surface 24. The trailing-edge component 18 further comprises a second recessed receiving surface 26 for receiving a second edge region 28 of the back skin 16, which comprises a second spanwise edge 30. This is shown in enlarged view FIG. 1A in further detail.

[0044] The trailing-edge component 18 tapers in a chordwise direction to form two spanwise flow surfaces 32 and 34. The first spanwise flow surface 32 extends the shape of the front skin 4 towards the trailing edge 8. The second flow surface 34 extends the shape of the back skin 16 towards the trailing edge 8. The receiving surfaces 24 and 26 are each delimited by a step 36 and 38, respectively. The front skin 4 abuts the step 36 of the first receiving surface 24, while the back skin 16 abuts the step 38 of the second receiving surface 26. Hence, a flush transition between the front skin 4 and the first flow surface 32 and between the back skin 16 and the second flow surface 34 is made. It is to be understood, that the dimensions of the steps 36 and 38 is adapted to conform the thickness of the front skin 4 and the back skin 16, respectively, including all optional material layers between the trailing-edge component 18 and the front skin 4 and the back skin 16, respectively.

[0045] The trailing edge component 18 comprises a wedge shape, while the cross-sectional profile comprises two legs 40 and 42, at which the receiving surfaces 24 and 26 are arranged. Both legs 40 and 42 enclose an intermediate space 44, i.e., a hollow space.

[0046] The flow body 2 of FIG. 1 exemplarily comprises a forward air chamber 46 enclosed by the front skin 4 and the spar 10. In a rear direction, a rear air chamber 48 is situated, which is in a fluid communication with the forward air chamber 46. For this, exemplarily openings 50 are provided in the spar 10. The rear air chamber 48 is defined by the spar 50, the front skin 4, the back skin 16 and the intermediate space 44.

[0047] The forward air chamber 46 and the rear air chamber 48 are used for an anti- or de-icing device, which may provide air at an elevated temperature into the forward air chamber 46. Thus, supplied air flows on an interior side of the front skin 4 and reaches the rear air chamber 48 by passing the openings 50. By providing the intermediate space 44, an active anti- or de-icing surface area of the front skin 4, which is marked with reference numeral 52, clearly extends into a rearward direction. Hence, anti- or de-icing is clearly improved in comparison with common design principles of leading-edge devices.

[0048] Furthermore, the trailing edge component 18 can be manufactured at clearly reduced costs compared to a honeycomb material construction. Altogether, flow body 2 according to the exemplary embodiment of FIG. 1 is clearly improved in terms of anti- or de-icing effect and manufacturing costs.

[0049] For the sake of completeness, a section 54 on the flow body 2 may be designated for attaching a lever for coupling the flow body 2 with an actuator or the like is exemplarily depicted. However, this is merely an example.

[0050] FIG. 2 shows another example of a flow body 56, which only comprises a front skin 58 having a curved shape. The trailing-edge component 18 is made in an extrusion process, by which a hole 59 is integrated into the cross-sectional profile. This allows a reduction of the weight and an improvement of the deformability to adapt the trailing-edge component 18 to the shape of the flow body 56. Of course, the trailing-edge component 18 may be made without the hole 59. Also, the trailing-edge component 18 of FIG. 1 may comprise the hole 59.

[0051] It is to be understood that also other shapes of the hole 59 are possible. Also, multiple holes 59, even with different shapes, are possible. To close the respective hole 59 at a most inboard or outboard end of the trailing-edge component 18, additional parts may be used. These may include clips or seals, an end rib of the flow body 56 or only a sealant, if possible.

[0052] In the example of FIG. 2, a first spanwise edge 60 and a second spanwise edge 62 abut the steps 36 and 38 of the trailing-edge component 18. Inside the flow body 56, a hollow space 64 is created, which may comprise stiffening elements, air chambers or any other features that are required.

[0053] FIG. 3 shows an aircraft 66, which comprises wings 68, a vertical tail plane 70, horizontal tail planes 72, engines 74 and winglets 76. These components may also comprise flow bodies that are designed according to the above description. For example, the wings 68 comprise leading-edge devices 78 having flow bodies 2 according to FIG. 1. Still further, an anti- or de-icing device 80 is provided, which is merely indicated with reference numeral 80. It may exemplarily be coupled with a bleed air port from at least one of the engines 74 for supplying air at an elevated temperature to the air chambers 46 and 48.

[0054] In addition, it should be pointed out that “comprising” does not exclude other elements or steps, and “a” or “an” does not exclude a plural number. Furthermore, it should be pointed out that characteristics or steps which have been described with reference to one of the above exemplary embodiments may also be used in combination with other characteristics or steps of other exemplary embodiments described above.

[0055] While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.

REFERENCE NUMERALS

[0056] 2 flow body [0057] 4 front skin [0058] 6 leading edge [0059] 8 trailing edge [0060] 10 spar [0061] 12 top section [0062] 14 bottom section [0063] 16 back skin [0064] 18 trailing-edge component [0065] 20 first spanwise edge [0066] 22 edge region [0067] 24 first receiving surface [0068] 26 second receiving surface [0069] 28 edge region [0070] 30 second spanwise edge [0071] 32 first spanwise flow surface [0072] 34 second spanwise flow surface [0073] 36 step [0074] 38 step [0075] 40 leg [0076] 42 leg [0077] 44 intermediate space [0078] 46 forward air chamber [0079] 48 rear air chamber [0080] 50 opening [0081] 52 anti- or de-icing surface area [0082] 54 section for attaching a lever [0083] 56 flow body [0084] 58 front skin [0085] 59 hole [0086] 60 first spanwise edge [0087] 62 second spanwise edge [0088] 64 hollow space [0089] 66 aircraft [0090] 68 wing [0091] 70 vertical tail plane [0092] 72 horizontal tail plane [0093] 74 engine [0094] 76 winglet [0095] 78 leading-edge device [0096] 80 anti- or de-icing device