Wing for an aircraft and aircraft

Abstract

A wing (3) for an aircraft (1) is disclosed, comprising a fixed wing (5), a foldable wingtip portion (9) mounted to the fixed wing (5) via a hinge (11) and rotatable between an extended position (15) and a folded position (17) about a hinge axis (13), and an actuation unit (19) for actuating the foldable wingtip portion (9) to move about the hinge axis (13). The object of the present invention is to provide a wing with a reduced complexity actuation unit, achieved by the wing (3) including a braking unit (21) for securing the foldable wingtip portion (9) in the folded position (17), and the braking unit (21) being formed separately from the actuation unit (19). This application also relates to an aircraft including the said wing.

Description

Technical Field

[0001] This invention relates to a wing for an aircraft, particularly a foldable wing comprising a fixed wing and a foldable wingtip portion. Another aspect of the invention relates to an aircraft including the wing. Background Technology

[0002] This wing includes a fixed wing for mounting to the fuselage, and a foldable wingtip portion mounted to the fixed wing via one or more hinges and rotatable about a hinge axis between an extended and a folded position. In the extended position, the foldable wingtip portion extends as a continuous extension of the fixed wing, preferably in a common plane with the fixed wing; in the folded position, the foldable wingtip portion extends upward or rearward to reduce the overall wingspan of the aircraft compared to the extended position. Specifically, when the foldable wingtip portion can be folded upward, the hinge axis extends in a horizontal plane and / or parallel to a chord line and / or parallel to the wing surface and / or the direction of flight of the aircraft. Alternatively, when the foldable wingtip portion can be folded rearward, the hinge axis extends in a vertical direction and / or in the depth direction and / or in a lateral or perpendicular direction to the wing surface.

[0003] In addition, the wing includes an actuation unit for actuating the foldable wingtip portion to move relative to the fixed wing about a hinge axis, i.e., for moving between an extended position and a folded position. The actuation unit can be formed in various ways, for example, as a rack and pinion drive, and can be mounted between the fixed wing and the foldable wingtip portion near the hinge axis.

[0004] A foldable wing was developed to reduce the space requirements of the aircraft during ground maneuvering and parking. Once the aircraft lands, the foldable wingtips fold upwards or backwards, thereby reducing the overall wingspan of the aircraft.

[0005] In the extended position, the folding wingtip is typically secured by a separate stop. However, in the folded position, when the aircraft is on the ground, the folding wingtip is typically held in place solely by an actuation unit. This means that the actuation unit not only needs to be designed to be movable but also needs to hold the folding wingtip in place. Summary of the Invention

[0006] Therefore, the object of the present invention is to provide a wing with an actuation unit having reduced complexity.

[0007] This objective is achieved by including a braking unit for securing the foldable wingtip portion in the folded position, wherein the braking unit is formed separately and independently from the actuation unit. This means that the braking unit can be actuated independently of the actuation unit. In this way, the actuation unit does not need to hold the foldable wingtip portion in the folded position, thus reducing design complexity. Furthermore, a failure of the actuation unit will not cause the foldable wingtip portion to move out of the folded position.

[0008] According to a preferred embodiment, the braking unit includes a first braking portion fixedly mounted to the fixed wing and a second braking portion fixedly mounted to the foldable wingtip portion. Preferably, the first and second braking portions are arranged such that when the foldable wingtip portion rotates about a hinge axis, they rotate relative to each other about a braking axis. Preferably, the first and second braking portions are configured such that they can engage at least when the foldable wingtip portion is in a folded position. However, the first and second braking portions can also engage in an intermediate position, such that the foldable wingtip portion can also be fixed in a position between a folded position and an extended position. Furthermore, the braking portions may have engagement surfaces extending laterally or parallel to the braking axis, such that they can engage movablely along or laterally to the braking axis. With such braking portions, a simple, flexible, and efficient brake can be formed.

[0009] According to another preferred embodiment, a control unit is provided to control the engagement and disengagement of the first and second braking components. The control unit may be part of a larger control unit for the entire foldable wing system, or it may be a separate control unit connected to the larger control unit for the entire foldable wing system. The control unit may also be connected to an actuator for braking to actuate the engagement and / or disengagement of the braking components. Such an actuator for braking may be an electric or hydraulic actuator.

[0010] According to another preferred embodiment, the first and second braking components are arranged such that the braking axis coincides with the hinge axis. In this way, no additional linkage mechanism is required to connect the braking components to the fixed wing and the folding wingtip respectively, thus forming a particularly simple and efficient braking unit.

[0011] According to an alternative embodiment, the first and second braking portions are arranged such that the braking axis is spaced apart from the hinge axis. The first braking portion is mounted on the fixed wing via a linkage mechanism. Alternatively or additionally, the second braking portion is mounted to the folding wingtip portion via a linkage mechanism. Such a linkage mechanism may include one or more pivot links.

[0012] In another preferred embodiment, a stop is provided to limit any movement of the foldable wingtip portion beyond the folded position. In this way, in the folded position, the foldable wingtip portion is secured in one direction by the stop, particularly to the upward direction, and in the opposite direction by the braking unit, particularly to the downward direction.

[0013] In yet another preferred embodiment, the braking unit is configured as an active brake, wherein the engagement and disengagement of the braking components are driven by electro- or hydraulic power, preferably by an actuator of the electro- or hydraulic brake. This active brake can be controlled with very high precision.

[0014] In particular, it is preferred that the braking unit is formed as a multi-disc brake, wherein the first braking portion and the second braking portion are formed as discs, the main surfaces of which engage with each other by movement along the braking axis. This multi-disc brake represents a very simple and efficient braking unit.

[0015] In another preferred embodiment, the braking unit is configured as a power-off brake, wherein the first and second braking portions engage in a powerless manner (i.e., without the need for external power), and the first and second braking portions are disengaged by electro- or hydraulic power, preferably by an actuator of the electro- or hydraulic brake. Since only the power to disengage the braking portions is required, the power-off brake involves a very simple and low-maintenance braking unit.

[0016] In particular, preferably, the braking unit is configured as a ratchet brake, which allows relative movement of the first braking portion and the second braking portion in the direction toward the folded position, and restricts relative movement of the first braking portion and the second braking portion in opposite directions from the folded position of the foldable wingtip portion back to the extended position. This ratchet brake represents a very simple, reliable, and efficient power-off brake.

[0017] Alternatively, preferably, the braking unit is configured as a freewheel brake, which allows relative movement of the first braking portion and the second braking portion in the direction toward the folded position, and restricts relative movement of the first braking portion and the second braking portion in opposite directions from the folded position of the foldable wingtip portion back to the extended position. This freewheel brake represents a very simple, reliable, and efficient power-off brake.

[0018] Alternatively, preferably, the braking unit is formed as a power-off disc brake, having a disc-shaped configuration of a first braking portion and a second braking portion engaged along their main surfaces, and allowing relative movement of the first and second braking portions in a direction toward the folded position, while restricting relative movement of the first and second braking portions in opposite directions from the folded position of the foldable wingtip portion back to the extended position. This power-off disc brake represents a very simple, reliable, and efficient power-off brake.

[0019] Another aspect of the invention relates to an aircraft comprising a wing according to any of the above embodiments. The aforementioned wing-related features and effects apply to this aircraft. Attached Figure Description

[0020] Preferred embodiments of the invention are described in more detail below with reference to the accompanying drawings. The drawings show:

[0021] Figure 1 This is a perspective view of an aircraft according to an embodiment of the present invention.

[0022] Figure 2 This is a schematic top view of an embodiment of the wing according to the present invention.

[0023] Figure 3 yes Figure 2 The side view of the wing shown indicates that the folding wingtip portion is in the extended position, and

[0024] Figure 4 yes Figure 2 The image shows a side view of the wing, with the foldable wingtip portion in the folded position. Detailed Implementation

[0025] Figure 1 An exemplary aircraft 1 according to an embodiment of the present invention is shown. The aircraft 1 includes a foldable wing 3, which includes a fixed wing 5 mounted to a fuselage 7 and a foldable wingtip portion 9 movably mounted to the fixed wing 5.

[0026] Figures 2 to 4 Showing more details Figure 1 The wing 3 of the aircraft 1 shown. The foldable wingtip portion 9 is mounted to the fixed wing 5 via hinge 11 and can be in the extended position 15 about the hinge axis 13 (see Figure 2 and 3 ) and fold position 17 (see Figure 4The foldable wingtip portion 9 rotates between the fixed wing 5 and the folded wing 5. In the extended position 15, the foldable wingtip portion 9 extends in the same plane as the fixed wing 5 as a continuous extension of the fixed wing 5. In the folded position 17, the foldable wingtip portion 9 extends upward to reduce the overall wingspan of the aircraft 1. The hinge axis 13 is parallel to the chord line and extends along the flight direction of the aircraft 1. Furthermore, the wing 3 includes an actuation unit 19 for moving the foldable wingtip portion 9 relative to the fixed wing 5 about the hinge axis 13.

[0027] The wing 3 includes a braking unit 21 for securing the foldable wingtip portion 9 in the folded position 17. The braking unit 21 is formed separately and independently from the actuation unit 19, such that the braking unit 21 can be actuated independently of the actuation unit 19.

[0028] The braking unit 21 includes a first braking portion 23 fixedly mounted to the fixed wing 5 and a second braking portion 25 fixedly mounted to the foldable wingtip portion 9. The first braking portion 23 and the second braking portion 25 are arranged such that when the foldable wingtip portion 9 rotates about the hinge axis 13, they rotate relative to each other about the braking axis 27. The first braking portion 23 and the second braking portion 25 are configured such that they can engage when the foldable wingtip portion 9 is in the folded position 17.

[0029] In this embodiment, the first braking portion 23 and the second braking portion 25 are arranged such that the braking axis 27 is spaced parallel to the hinge axis 13, and the second braking portion 25 is mounted to the foldable wingtip portion 9 via a linkage mechanism 29. However, in other embodiments, the first braking portion 23 and the second braking portion 25 may be arranged such that the braking axis 27 coincides with the hinge axis 13.

[0030] The first braking part 23 can be mounted to the fixed wing 5 via the linkage mechanism 29, and / or the second braking part 25 can be mounted to the foldable wingtip part 9 via the linkage mechanism 29.

[0031] In this embodiment, the braking unit 21 is configured as an active brake, wherein the engagement and disengagement of the braking portions 23, 25 are driven by electric or hydraulic power. More specifically, the braking unit 21 is configured as a multi-disc brake, wherein the first braking portion 23 and the second braking portion 25 are formed as discs whose main surfaces engage with each other by movement along the braking axis 27. However, in other embodiments, the braking unit 21 may also be configured as a power-off brake, such as a ratchet brake or a freewheel brake.

[0032] Furthermore, the wing 3 includes a control unit 31 for controlling the engagement and disengagement of the first braking portion 23 and the second braking portion 25. The wing 3 also includes a stop 33 to limit the movement of the foldable wingtip portion 9 beyond the folded position 17, such that in the folded position 17, the foldable wingtip portion 9 is fixed in one direction by the stop 33 and in the opposite direction by the braking unit 21.

Claims

1. A wing (3) for an aircraft (1), comprising: Fixed-wing (5) A foldable wingtip portion (9), which is mounted to the fixed wing (5) via a hinge (11) and is rotatable about the hinge axis (13) between an extended position (15) and a folded position (17). Actuation unit (19), the actuation unit being used to actuate the foldable wingtip portion (9) to move about the hinge axis (13), Its features are, The wing (3) includes a braking unit (21) for securing the foldable wingtip portion (9) in the folded position (17). The braking unit (21) includes a first braking portion (23) and a second braking portion (25) formed as a disc. The main surfaces of the disc engage with each other by moving along the braking axis (27). The engagement and disengagement of the first braking part (23) and the second braking part (25) are driven by electric or hydraulic power. The braking unit (21) and the actuation unit (19) are formed separately, and The first braking portion (23) and the second braking portion (25) are configured such that the braking axis (27) coincides with the hinge axis (13).

2. The wing according to claim 1, wherein, The first braking part (23) is mounted to the fixed wing (5), and the second braking part (25) is mounted to the foldable wingtip part (9). The first braking portion (23) and the second braking portion (25) are configured such that when the foldable wingtip portion (9) rotates about the hinge axis (13), the first braking portion and the second braking portion rotate relative to each other about the braking axis (27), and The first braking portion (23) and the second braking portion (25) are configured such that when the foldable wingtip portion (9) is in the folded position (17), the first braking portion and the second braking portion can engage.

3. The wing according to claim 2, wherein, A control unit (31) is provided to control the engagement and disengagement of the first braking part (23) and the second braking part (25).

4. The wing according to claim 2 or 3, in, The first braking part (23) is mounted to the fixed wing (5) via a linkage mechanism (29), and / or the second braking part (25) is mounted to the foldable wingtip part (9) via a linkage mechanism (29).

5. The wing according to any one of claims 1 to 4, wherein, A stop (33) is provided to restrict the movement of the foldable wingtip portion (9) beyond the folding position (17), such that the foldable wingtip portion (9) is fixed in one direction by the stop (33) at the folding position (17) and fixed in the opposite direction by the braking unit (21).

6. The wing according to any one of claims 1 to 5, wherein, The braking unit (21) is configured as a power-off brake, wherein the first braking part (23) and the second braking part (25) are engaged in a powerless manner, and the first braking part (23) and the second braking part (25) are disengaged by electric or hydraulic power.

7. The wing according to claim 6, wherein, The braking unit (21) is configured as a ratchet brake, which allows the first braking portion (23) and the second braking portion (25) to move relative to each other in the direction toward the folded position (17), and restricts the relative movement of the first braking portion (23) and the second braking portion (25) toward the extended position (15) of the foldable wingtip portion (9) in opposite directions.

8. The wing according to claim 6, wherein, The braking unit (21) is configured as a freewheel brake, which allows the first braking portion (23) and the second braking portion (25) to move relative to each other in the direction toward the folded position (17), and restricts the relative movement of the first braking portion (23) and the second braking portion (25) toward the extended position (15) of the foldable wingtip portion (9) in opposite directions.

9. The wing according to claim 6, wherein, The braking unit (21) is configured as a power-off disc brake that allows the first braking portion (23) and the second braking portion (25) to move relative to each other in the direction toward the folded position (17), while restricting the relative movement of the first braking portion (23) and the second braking portion (25) from the folded position (17) of the foldable wingtip portion (9) back to the extended position (15) in opposite directions.

10. A wing (3) for an aircraft (1), comprising: Fixed-wing (5) A foldable wingtip portion (9), which is mounted to the fixed wing (5) via a hinge (11) and is rotatable about the hinge axis (13) between an extended position (15) and a folded position (17). Actuation unit (19), the actuation unit being used to actuate the foldable wingtip portion (9) to move about the hinge axis (13), Its features are, The wing (3) includes a braking unit (21) for securing the foldable wingtip portion (9) in the folded position (17). The braking unit (21) includes a first braking portion (23) and a second braking portion (25) formed as a disc. The main surfaces of the disc engage with each other by moving along the braking axis (27). The engagement and disengagement of the first braking part (23) and the second braking part (25) are driven by electric or hydraulic power. The braking unit (21) and the actuation unit (19) are formed separately, and The first braking portion (23) and the second braking portion (25) are configured such that the braking axis (27) is spaced apart from the hinge axis (13) in parallel.

11. An aircraft (1) comprising a wing (3) according to any one of claims 1 to 10.

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