Flap support, wing and aircraft

Abstract

A flap support for supporting a flap of a wing of an aircraft is disclosed, the flap support comprising a load-bearing fairing and comprising a reinforcing structure which is at least partially received in an interior space of the fairing and is mounted to a first side wall portion and a second side wall portion of the fairing, wherein the fairing comprises a front attachment device configured for attachment to a main wing, wherein the reinforcing structure comprises a rear attachment device configured for attachment to the main wing, and wherein the flap support further comprises a hinge device configured for forming a hinged connection with the flap. By having the hinge device form part of the reinforcing structure, the object of providing a particularly strong and at the same time lightweight flap support is achieved.

Description

Technical Field

[0001] This invention relates to a flap support for supporting flaps of an aircraft wing, particularly for pivotally supporting a high-lift trailing-edge flap as it moves between a retracted and extended position. Another aspect of the invention relates to an aircraft wing including such a flap support, and to an aircraft including such a wing. Background Technology

[0002] The flap support includes a fairing that at least partially bears the load. The fairing extends along a longitudinal axis between a forward end and a rear end. Furthermore, the fairing has a U-shaped cross-section transverse to the longitudinal axis, thereby including a first sidewall portion, a second sidewall portion opposite to the first sidewall portion, and a bottom wall portion connecting the first and second sidewall portions. The fairing partially surrounds an internal space that is open to the environment opposite to the bottom wall portion.

[0003] The flap support also includes a reinforcing structure, which is preferably formed as an integral component. The reinforcing structure is at least partially received in the interior space of the fairing, and is mounted to both the first and second sidewall portions at the inner surfaces of the first and second sidewall portions facing the interior space to reinforce the fairing.

[0004] The fairing includes, preferably in a region of the front end, a forward attachment device configured for attachment to the main wing. The reinforcing structure includes a rear attachment device spaced apart from the forward attachment device and further close to the rear end of the fairing, and the rear attachment device is configured for attachment to the main wing at a location spaced apart from the forward attachment device.

[0005] The flap support also includes, preferably in the region of the rear end of the fairing, a hinge device configured to form, preferably via at least one connecting element pivotally mounted to the hinge device and the flap, an articulated connection with the flap.

[0006] Such flap support components are known in the art, for example from US 9,926,069B2, wherein the hinge is formed at the rear end of the fairing. Summary of the Invention

[0007] The object of this invention is to provide a particularly robust yet lightweight flap support.

[0008] This objective is achieved by making the hinge device an integral part of the reinforcing structure. Preferably, the hinge device is integrally formed with the reinforcing structure. In this way, the load from the flap is not directly introduced into the fairing, but rather into the reinforcing structure, and the load from the reinforcing structure is gradually transferred to the fairing. This enables the flap support to achieve a particularly high and fault-protected load-bearing capacity.

[0009] According to a preferred embodiment, the fairing has a streamlined outer surface. In this way, the flap support minimizes aerodynamic drag.

[0010] According to another preferred embodiment, the rectifier housing is made of fiber-reinforced plastic (FRP) material, preferably carbon fiber reinforced plastic (CFRP) material. FRP material provides high strength with a small weight, allowing the rectifier housing to safely transmit high loads while maintaining a minimum weight.

[0011] According to another preferred embodiment, the reinforcing structure is made of a metallic material, preferably aluminum. By reinforcing the FRP rectifier shell with a metallic reinforcing structure, a hybrid structure of metal and FRP is formed. In this way, redundant load paths are introduced into the flap support. Furthermore, the metallic material is particularly suitable for receiving articulated loads from the flaps.

[0012] According to another preferred embodiment, the reinforcing structure includes a first side section mounted to a first sidewall portion, a second side section mounted to a second sidewall portion, and a structural bridge connecting the first and second side sections and preferably integrally formed with them. The first and second side sections form two separate load paths, and the structural bridge transfers the load between the first and second side sections and reinforces the rectifier shell in the lateral direction.

[0013] Specifically, preferably, the first side section has a first front portion that rests against and is mounted to the first sidewall portion, and a first rear portion that is detached from and spaced apart from the first sidewall portion. Similarly, the second side section has a second front portion that rests against and is mounted to the second sidewall portion, and a second rear portion that is detached from and spaced apart from the second sidewall portion. The first front portion is preferably mounted to the first sidewall portion in a planar manner, preferably by a plurality of two-dimensionally distributed rivets. Likewise, the second front portion is preferably mounted to the second sidewall portion in a planar manner, preferably by a plurality of two-dimensionally distributed rivets. In this way, loads from the first and second rear portions, such as loads introduced by the hinge mechanism, can be smoothly and uniformly transmitted to the rectifier housing via the first and second front portions.

[0014] Particularly preferred is that the structural bridge connects the first rear portion and the second rear portion. In this way, the first rear portion and the second rear portion abut against each other in the lateral direction, specifically to receive loads introduced from the hinged device.

[0015] Preferably, the hinge mechanism is located at the first rear portion and the second rear portion. Specifically, preferably, the first rear portion includes a first hinge lug, and the second rear portion includes a second hinge lug. In this way, each hinge lug is connected to a separate load path.

[0016] Specifically, preferably, the fairing extends beyond the hinge at its rear end in a manner that a first sidewall portion is spaced apart from a first rear portion and a second sidewall portion is spaced apart from a second rear portion. Therefore, these portions of the fairing extending between the rear ends and mounted to the reinforcing structure do not transmit any load and are therefore not load-bearing portions of the fairing. Preferably, the first and second sidewall portions include orifices aligned with the first and second hinge lugs to receive corresponding hinge bolts extending through the first and second hinge lugs. Preferably, the diameter of the orifices is larger than the diameter of the hinge lugs, thereby preventing load transfer between the hinge bolts and the orifices. In this way, the load from the flaps is transmitted only by the reinforcing structure until the reinforcing structure is mounted to the fairing at the first and second front portions.

[0017] According to a preferred embodiment, the rear attachment device includes a first attachment lug formed at a first side section and projecting upward from the first side section. The first attachment lug is preferably formed at a first front section, such that it is formed by both a reinforcing structure and a rectifier housing resting against each other. Furthermore, the rear attachment device includes a second attachment lug formed at a second side section and projecting upward from the second side section. The second attachment lug is preferably formed at a second front section, such that it is formed by both a reinforcing structure and a rectifier housing resting against each other. In this way, a simple and robust rear attachment device is directly formed by the reinforcing structure itself.

[0018] According to an alternative preferred embodiment, the reattachment device includes a first barrel-shaped nut mounting member disposed on a first side section and a second barrel-shaped nut mounting member disposed on a second side section. This barrel-shaped nut mounting member is a simple and reliable installation option.

[0019] Preferably, an additional structural bridge may be provided between the reinforcing structure and the front end of the rectifier shell to form further reinforcement between the first sidewall portion and the second sidewall portion.

[0020] According to another preferred embodiment, the front attachment device includes a plurality of ribs formed in the fairing and extending transversely along the longitudinal axis. The ribs include holes aligned along the longitudinal axis to receive corresponding bolts for mounting to the main wing. In this way, a simple and reliable front attachment device is formed.

[0021] Another aspect of the invention relates to a wing for an aircraft. The wing includes a main wing, flaps, and flap supports according to any of the embodiments described above. A front attachment device and a rear attachment device are attached to the main wing, preferably at positions spaced apart from each other along the longitudinal axis. The flaps are pivotally connected to a hinge device, preferably via one or more connecting elements. The features and advantages detailed above in conjunction with the flap supports apply to this wing.

[0022] Another aspect of the invention relates to an aircraft comprising a wing according to the embodiments described above. The features and advantages detailed above in conjunction with the flap support and the wing are applicable to this aircraft. Attached Figure Description

[0023] In the following description, preferred embodiments of the invention will be further described in detail with the aid of the accompanying drawings. The drawings show:

[0024] Figure 1 This is a perspective view of an aircraft according to an embodiment of the present invention;

[0025] Figure 2 This is a perspective view of the flap support member according to the first embodiment of the present invention;

[0026] Figure 3 This is a perspective view of a flap support member according to a first embodiment of the present invention; and

[0027] Figure 4 This is a perspective view of a flap support according to another embodiment. Detailed Implementation

[0028] exist Figure 1 The image shows an aircraft 1 according to the present invention. The aircraft 1 includes a fuselage 3 and wings 5 ​​mounted to the fuselage 3. Each wing 5 includes a main wing 7, a plurality of flaps 9, and a plurality of flap supports 11, the plurality of flaps 9 being mounted to the main wing 7, and the plurality of flap supports 11 being mounted to the main wing 7 to hingedly support the flaps 9 as they move between a retracted position and an extended position. The flaps 9 are high-lift trailing-edge flaps.

[0029] Figure 2 As shown Figure 1The first embodiment of the flap support 11 used in the aircraft 1 shown is illustrated. The flap support 11 includes a load-bearing fairing 13. The fairing 13 extends along a longitudinal axis 15 between a front end portion 17 and a rear end portion 19. Furthermore, the fairing 13 has a U-shaped cross-section transverse to the longitudinal axis 15, thereby including a first sidewall portion 21, a second sidewall portion 23 opposite to the first sidewall portion 21, and a bottom wall portion 25 connecting the first sidewall portion 21 and the second sidewall portion 23. The fairing 13 partially surrounds an internal space 27, which is open to the environment opposite to the bottom wall portion 25. The fairing 13 is made of carbon fiber reinforced plastic (CFRP) material and has a streamlined outer surface 29.

[0030] The flap support 11 also includes a reinforcing structure 31, which is received in the internal space 27 of the rectifier shell 13 and mounted to both the first sidewall portion 21 and the second sidewall portion 23 to reinforce the rectifier shell 13. The reinforcing structure 31 is made of polished aluminum.

[0031] The fairing 13 includes a forward attachment device 33 configured for attachment to the main wing 7 in the region of the forward end portion 17. The forward attachment device 33 includes a plurality of ribs 35 formed in the fairing 13 and extending transversely through the longitudinal axis 15. The ribs 35 include holes 37 aligned along the longitudinal axis 15 to receive corresponding bolts (not shown) for mounting to the main wing 7.

[0032] The flap support 11 also includes a hinge 39 in the region of the rear end 19 of the fairing 13. The hinge 39 is configured to form a hinged connection with the flap 9 via one or more connecting elements (not shown) pivotally mounted to the hinge 39 and the flap 9. The hinge 39 forms part of the reinforcing structure 31 and is integrally formed with the reinforcing structure 31.

[0033] The reinforcing structure 31 includes a first side section 41 mounted to the first side wall portion 21, a second side section 43 mounted to the second side wall portion 23, and a structural bridge 45 connecting the first side section 41 and the second side section 43. The first side section 41 has a first front portion 47 resting against and mounted to the first side wall portion 21, and a first rear portion 49 detached from and spaced apart from the first side wall portion 21. Similarly, the second side section 43 has a second front portion 51 resting against and mounted to the second side wall portion 23, and a second rear portion 53 detached from and spaced apart from the second side wall portion 23. The first front portion 47 is mounted to the first side wall portion 21 in a planar manner by a plurality of two-dimensionally distributed rivets 55. Likewise, the second front portion 51 is preferably mounted to the second side wall portion 23 in a planar manner by a plurality of two-dimensionally distributed rivets 55.

[0034] Structural bridge 45 connects the first rear portion 49 and the second rear portion 53. A hinge device 39 is provided at the first rear portion 49 and the second rear portion 53. The first rear portion 49 includes a first hinge lug 57, and the second rear portion 53 includes a second hinge lug 59.

[0035] The rectifier housing 13 extends beyond the hinge device 39 at its rear end 19, spaced apart by a first sidewall portion 21 and a first rear portion 49, and by a second sidewall portion 23 and a second rear portion 53. Therefore, these portions of the rectifier housing 13 extending between the rear ends 19 and mounted to the reinforcing structure 31 (indicated by shaded areas) do not transmit any load and are therefore not load-bearing portions of the rectifier housing 13. The first sidewall portion 21 and the second sidewall portion 23 include an aperture 61 aligned with a first hinge lug 57 and a second hinge lug 59 to receive corresponding hinge bolts (not shown) extending through the first hinge lug 57 and the second hinge lug 59. The diameter of the aperture 61 is larger than the diameter of the hinge lugs 57, 59, thereby preventing load transfer between the hinge bolts and the aperture 61.

[0036] The reinforcing structure 31 includes a rear attachment device 63, which is spaced apart from the front attachment device 33 and further close to the rear end 19 of the fairing 13, and is configured to attach to the main wing 7 at a position spaced apart from the front attachment device 33. Figure 2 In the embodiment shown, the rear attachment device 63 includes a first barrel nut mounting member 65 disposed on the first side section 41 and a second barrel nut mounting member 67 disposed on the second side section 43.

[0037] Furthermore, an additional structural bridge 69 is provided between the reinforcing structure 31 and the front end 17 of the rectifier housing 13 to provide further reinforcement between the first sidewall portion 21 and the second sidewall portion 23. The rear attachment device 63, namely the first barrel nut mount 65 and the second barrel nut mount 67, is also supported at the additional structural bridge 69.

[0038] Figure 3 It shows in Figure 1 An alternative embodiment of the flap support 11 used at the aircraft 1 shown. This embodiment corresponds to the following: except that the aft attachment 63 includes a first attachment lug 71 and a second attachment lug 73 instead of a first barrel nut mount 65 and a second barrel nut mount 67. Figure 2The embodiment shown. A first attachment lug 71 is formed at a first side section 41 and protrudes upward from the first side section 41. The first attachment lug 71 is formed at a first front section 47 such that the first attachment lug 71 is formed by both the reinforcing structure 31 and the rectifier shell 13 resting against each other. A second attachment lug 73 is formed at a second side section 43 and protrudes upward from the second side section 43. The second attachment lug 73 is formed at a second front section 51 such that the second attachment lug 73 is formed by both the reinforcing structure 31 and the rectifier shell 13 resting against each other.

[0039] Figure 4 Another embodiment of the flap support 11 is shown, which is related to Figure 3 The embodiment shown is similar, but has a reinforcing structure 31 composed of multiple separate parts. Specifically, the hinge device 39, particularly the first hinge lug 57 and the second hinge lug 59, is reinforced by a metal hinge lug reinforcement 75. Furthermore, the first attachment lug 71 and the second attachment lug 73 are reinforced by the first metal attachment lug reinforcement 77 and the second metal attachment lug reinforcement 79. Additionally, multiple metal bridges 81 are provided connecting the first sidewall portion 21 and the second sidewall portion 23.

Claims

1. A flap support (11) for supporting flaps (9) of a wing (5) of an aircraft (1), the flap support (11) comprising: A load-bearing rectifier shell (13) extends along a longitudinal axis (15) between a front end (17) and a rear end (19), and the rectifier shell (13) has a U-shaped cross-section transverse to the longitudinal axis (15), thereby including a first sidewall portion (21), a second sidewall portion (23) opposite to the first sidewall portion (21), and a bottom wall portion (25) connecting the first sidewall portion (21) and the second sidewall portion (23), wherein the rectifier shell (13) partially surrounds an internal space (27), and A reinforcing structure (31) is at least partially received in the interior space (27) and mounted to the first sidewall portion (21) and the second sidewall portion (23). The rectifier shell (13) includes a front attachment device (33) located at the front end of the reinforcing structure (31) and configured for attachment to the main wing (7). The reinforcing structure (31) includes a rear attachment device (63) spaced apart from the front attachment device (33) and further close to the rear end (19) of the rectifier shell (13), and the rear attachment device (63) is configured to be attached to the main wing (7). The flap support (11) further includes a hinge device (39) located at the rear end of the reinforcing structure (31), wherein the hinge device (39) is configured to form a hinged connection with the flap (9). Its features are, The reinforcing structure (31) further includes a first side section (41) mounted to the first sidewall portion (21), a second side section (43) mounted to the second sidewall portion (23), and a first structural bridge (45) connecting the first side section (41) and the second side section (43), wherein a second structural bridge (69) is provided between the reinforcing structure (31) and the front end portion (17) of the rectifier housing (13), and wherein the second structural bridge (69) extends from the front end portion of the rear attachment device (63) to the rear end portion of the front attachment device (33), and The hinge device (39) forms part of the reinforcing structure (31), wherein the load from the flap (9) is introduced into the reinforcing structure (31) and indirectly transmitted to the rectifier shell (13) via the reinforcing structure (31), rather than being directly introduced into the rectifier shell (13).

2. The flap support member according to claim 1, wherein, The rectifier shell (13) has a streamlined outer surface (29).

3. The flap support member according to claim 1 or 2, wherein, The rectifier housing (13) is made of fiber-reinforced plastic material.

4. The flap support member according to claim 1 or 2, wherein, The reinforcing structure (31) is made of metallic material.

5. The flap support member according to claim 1 or 2, wherein, The first side section (41) has a first front portion (47) that rests against and is mounted to the first side wall portion (21) and a first rear portion (49) that is detached from the first side wall portion (21). The second side section (43) has a second front portion (51) that rests against the second side wall portion (23) and is mounted to the second side wall portion (23), and a second rear portion (53) that is detached from the second side wall portion (23).

6. The flap support member according to claim 5, wherein, The first structural bridge (45) connects the first rear portion (49) and the second rear portion (53).

7. The flap support member according to claim 5, wherein, The hinge device (39) is disposed at the first rear portion (49) and the second rear portion (53).

8. The flap support member according to claim 7, wherein, The first rear portion (49) includes a first hinge lug (57), and the second rear portion (53) includes a second hinge lug (59).

9. The flap support member according to claim 8, wherein, The rectifier housing (13) extends beyond the hinge device (39) such that the first sidewall portion (21) is spaced apart from the first rear portion (49) and the second sidewall portion (23) is spaced apart from the second rear portion (53), wherein the first sidewall portion (21) and the second sidewall portion (23) include openings (61) aligned with the first hinge lug (57) and the second hinge lug (59).

10. The flap support member according to any one of claims 1, 2, 6 to 9, wherein, The rear attachment device (63) includes a first attachment lug (71) formed on the first side section (41) and projecting upward from the first side section (41), and a second attachment lug (73) formed on the second side section (43) and projecting upward from the second side section (43).

11. The flap support member according to any one of claims 1, 2, 6 to 9, wherein, The rear attachment device (63) includes a first barrel nut mounting member (65) disposed on the first side section (41) and a second barrel nut mounting member (67) disposed on the second side section (43).

12. The flap support member according to any one of claims 1, 2, 6 to 9, wherein, The front attachment device (33) includes a plurality of ribs (35) formed in the rectifier shell (13) and extending transversely to the longitudinal axis (15), wherein the ribs (35) include holes (37) aligned along the longitudinal axis (15) to receive corresponding bolts mounted to the main wing (7).

13. A wing (5) for an aircraft (1), said wing (5) comprising: main wing (7), flaps (9), and The flap support (11) according to any one of claims 1 to 12. The front attachment device (33) and the rear attachment device (63) are attached to the main wing (7), and The flap (9) is pivotally connected to the hinge device (39).

14. An aircraft (1) comprising a wing (5) according to claim 13.

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