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CN-110395383-B - Wing for an aircraft and aircraft

CN110395383BCN 110395383 BCN110395383 BCN 110395383BCN-110395383-B

Abstract

A wing (3) for an aircraft (1) is disclosed, comprising a stationary wing (5), a foldable wing tip section (9) mounted to the stationary wing (5) via a hinge (11) and rotatable about a hinge axis (13) between an extended position (15) and a folded position (17), and an actuation unit (19) for actuating the foldable wing tip section (9) to move about the hinge axis (13). The object of the application is to provide a wing with an actuation unit of reduced complexity and which is achieved in that the wing (3) comprises a braking unit (21) for securing the foldable wing tip part (9) in the folded position (17), and that the braking unit (21) is formed separately from the actuation unit (19). The application also relates to an aircraft comprising said wing.

Inventors

  • CHRISTIAN LORENZ

Assignees

  • 空中客车德国运营有限责任公司

Dates

Publication Date
20260505
Application Date
20190424
Priority Date
20180424

Claims (11)

  1. 1. A wing (3) for an aircraft (1), comprising: a fixed wing (5), A foldable wingtip portion (9) mounted to the fixed wing (5) via a hinge (11) and rotatable about a hinge axis (13) between an extended position (15) and a folded position (17), and An actuation unit (19) for actuating the foldable wing tip section (9) to move about the hinge axis (13), It is characterized in that the method comprises the steps of, The wing (3) comprises a braking unit (21) for securing the foldable wing tip part (9) in the folded position (17), the braking unit (21) comprising a first braking portion (23) and a second braking portion (25) formed as discs, the main surfaces of the discs being engaged with each other by movement along a braking axis (27), Wherein the engagement and disengagement of the first braking portion (23) and the second braking portion (25) is driven by electric or hydraulic power, The braking unit (21) is formed separately from the actuation unit (19), and Wherein the first braking portion (23) and the second braking portion (25) are arranged such that the braking axis (27) coincides with the hinge axis (13).
  2. 2. The wing according to claim 1, wherein the first braking portion (23) is mounted to the fixed wing (5) and the second braking portion (25) is mounted to the foldable wing tip portion (9), Wherein the first (23) and second (25) braking portions are arranged to rotate relative to each other about the braking axis (27) when the foldable wing tip portion (9) rotates about the hinge axis (13), and Wherein the first and second braking portions (23, 25) are configured to be engageable when the foldable wing tip portion (9) is in the folded position (17).
  3. 3. Wing according to claim 2, wherein a control unit (31) is provided to control the engagement and disengagement of the first braking portion (23) and the second braking portion (25).
  4. 4. The wing according to claim 2 or 3, Wherein the first braking portion (23) is mounted to the stationary wing (5) via a linkage (29) and/or the second braking portion (25) is mounted to the foldable wing tip portion (9) via a linkage (29).
  5. 5. A wing according to any one of claims 1 to 4, wherein a stop (33) is provided for limiting the movement of the foldable wing tip part (9) beyond the folded position (17) such that the foldable wing tip part (9) is fixed in one direction in the folded position (17) by the stop (33) and in the opposite direction by the brake unit (21).
  6. 6. The wing according to any one of claims 1 to 5, wherein the brake unit (21) is formed as a power-off brake, wherein the first brake portion (23) and the second brake portion (25) are engaged in an unpowered manner, and wherein the first brake portion (23) and the second brake portion (25) are separated by an electric or hydraulic power drive.
  7. 7. The wing according to claim 6, wherein the brake unit (21) is formed as a ratchet brake allowing a relative movement of the first brake portion (23) and the second brake portion (25) in a direction towards the folded position (17) and limiting a relative movement of the first brake portion (23) and the second brake portion (25) in opposite directions towards the extended position (15) of the foldable wing tip portion (9).
  8. 8. The wing according to claim 6, wherein the brake unit (21) is formed as a free wheel brake allowing a relative movement of the first brake part (23) and the second brake part (25) in a direction towards the folded position (17) and limiting a relative movement of the first brake part (23) and the second brake part (25) in opposite directions towards the extended position (15) of the foldable wing tip part (9).
  9. 9. The wing according to claim 6, wherein the braking unit (21) is formed as a loss of disc brake allowing a relative movement of the first braking portion (23) and the second braking portion (25) in a direction towards the folded position (17) while limiting a relative movement of the first braking portion (23) and the second braking portion (25) in an opposite direction from the folded position (17) of the foldable wing tip portion (9) back to the extended position (15).
  10. 10. A wing (3) for an aircraft (1), comprising: a fixed wing (5), A foldable wingtip portion (9) mounted to the fixed wing (5) via a hinge (11) and rotatable about a hinge axis (13) between an extended position (15) and a folded position (17), and An actuation unit (19) for actuating the foldable wing tip section (9) to move about the hinge axis (13), It is characterized in that the method comprises the steps of, The wing (3) comprises a braking unit (21) for securing the foldable wing tip part (9) in the folded position (17), the braking unit (21) comprising a first braking portion (23) and a second braking portion (25) formed as discs, the main surfaces of the discs being engaged with each other by movement along a braking axis (27), Wherein the engagement and disengagement of the first braking portion (23) and the second braking portion (25) is driven by electric or hydraulic power, The braking unit (21) is formed separately from the actuation unit (19), and Wherein the first detent portion (23) and the second detent portion (25) are arranged such that the detent axis (27) is spaced apart parallel to the hinge axis (13).
  11. 11. An aircraft (1) comprising a wing (3) according to any one of claims 1 to 10.

Description

Wing for an aircraft and aircraft Technical Field The present invention relates to a wing for an aircraft, in particular a foldable wing, comprising a fixed wing and a foldable wing tip section. Another aspect of the invention relates to an aircraft comprising the wing. Background Such a wing comprises a fixed wing for mounting to the fuselage, and a foldable wing tip portion mounted to the fixed wing via one or more hinges and rotatable about a hinge axis between an extended position in which the foldable wing tip portion extends as a continuous extension of the fixed wing, preferably in a common plane with the fixed wing, and a folded position in which the foldable wing tip portion extends upwardly or rearwardly so as to reduce the overall span of the aircraft compared to the extended position. In particular, when the foldable wing tip section is foldable upwards, the hinge axis extends in a horizontal plane and/or parallel to the chord line and/or parallel to the flight direction of the airfoil and/or the aircraft. Or when the foldable wing tip section is foldable back, the hinge axis extends in a vertical direction and/or in a wing depth direction and/or in a direction transverse or perpendicular to the wing surface. Furthermore, the wing comprises an actuation unit for actuating the foldable wing tip part for movement about the hinge axis relative to the fixed wing, i.e. for movement between an extended position and a folded position. The actuation unit may be formed in various ways, for example as a rack and pinion gear, and may be mounted between the stationary wing and the foldable wing tip section near the hinge axis. Foldable wings have been developed to reduce the space requirements of the aircraft during maneuvering and parking on the ground. Once the aircraft lands, the foldable wingtip portion of the wing is folded up or back, thereby reducing the overall span of the aircraft. In the extended position, the foldable wing tip section is typically secured by a separate stop means. However, in the folded position, the foldable wingtip portion is typically held only by the actuation unit when the aircraft is on the ground. This means that the actuation unit not only needs to be designed to be movable but also needs to hold the foldable wing tip part in place. Disclosure of Invention It is therefore an object of the present invention to provide a wing with an actuation unit of reduced complexity. This object is achieved in that the wing comprises a braking unit for securing the foldable wing tip section in the folded position, wherein the braking unit is formed separately and independently from the actuation unit. This means that the brake unit can be actuated separately and apart from the actuation unit. In this way, the actuation unit does not need to hold the foldable wing tip part in the folded position, and thus the complexity of the design can be reduced. Furthermore, failure of the actuation unit does not result in the foldable wing tip section moving out of the folded position. According to a preferred embodiment, the braking unit comprises a first braking portion fixedly mounted to the stationary wing and a second braking portion fixedly mounted to the foldable wing tip portion. Preferably, the first and second braking portions are arranged such that when the foldable wing tip portion is rotated about the hinge axis, they rotate relative to each other about the braking axis. Preferably, the first and second braking portions are configured such that they are engageable at least when the foldable wing tip portion is in the folded position. However, the first and second braking portions may also be engaged in an intermediate position, such that the foldable wing tip portion may also be secured in a position between the folded and extended positions. Furthermore, the braking portions may have engagement surfaces extending transversely or parallel to the braking axis such that they may be in movable engagement along or transversely to the braking axis. By means of such a braking portion, a simple, flexible and efficient brake can be formed. According to another preferred embodiment, a control unit is provided to control the engagement and disengagement of the first and second brake portions. The control unit may be part of the entire collapsible wing system control unit or may be a separate control unit connected to the entire collapsible wing system control unit. The control unit may also be connected to an actuator for braking to actuate engagement and/or disengagement of the braking components. Such an actuator for braking may be an electric or hydraulic actuator. According to a further preferred embodiment, the first and second detent portions are arranged such that the detent axis coincides with the hinge axis. In this way no additional linkage is required to connect the braking section to the fixed wing and the foldable wing tip section respectively, resulting in a particularly simple and