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CN-121990154-A - Wing, leading edge high lift assembly for an aircraft and aircraft

CN121990154ACN 121990154 ACN121990154 ACN 121990154ACN-121990154-A

Abstract

A wing for an aircraft, a leading edge high lift assembly and an aircraft are disclosed, the wing comprising a main wing and a leading edge high lift assembly, the leading edge high lift assembly comprising a slat and a linkage assembly movably connecting the slat to the main wing such that the slat is movable between a retracted position, a first extended position and a second extended position, wherein the linkage assembly comprises an elongate slat track, a first end and/or a middle portion of the slat track being mounted to the slat, the slat track being mounted to the main wing by roller bearing means. The object is achieved of providing a wing with a beneficial aerodynamic performance to noise ratio resulting from the extension of the slat, wherein the slat track and the roller bearing are configured such that in the retracted position and the first extended position the slat rests against the main wing, and in the second extended position a gap is formed between the trailing edge of the slat and the leading edge of the main wing.

Inventors

  • Bernhard Schliepf
  • Dennis Cray

Assignees

  • 空中客车德国运营有限责任公司

Dates

Publication Date
20260508
Application Date
20251105
Priority Date
20241107

Claims (15)

  1. 1. A wing (3) for an aircraft (1), comprising: A main wing (5), and A leading edge high lift assembly (6), the leading edge high lift assembly (6) comprising: slat (7), and -A connection assembly (9), the connection assembly (9) movably connecting the slat (7) to the main wing (5) such that the slat (7) is movable between a retracted position (11), a first extended position (13) and a second extended position (15), Wherein the connection assembly (9) comprises an elongated slat track (17), the slat track (17) extending along a track longitudinal axis (19) between a first end (21) and a second end (23) and having an intermediate portion (25) between the first end (21) and the second end (23), Wherein the first end portion (21) and/or the intermediate portion (25) of the slat track (17) is mounted to the slat (7), Wherein the slat track (17) is mounted to the main wing (5) by roller bearing means (27) such that the slat track (17) is movable along the track longitudinal axis (19), Wherein the roller bearing arrangement (27) comprises a plurality of bearing units (34 a to 34 c), each of the bearing units (34 a to 34 c) being mounted to the main wing (5) and having a bearing surface (22), the bearing surface (22) being for engagement with an engagement surface (35) provided to the slat track (17), Wherein a plurality of the bearing units (34 a to 34 c) comprises at least a first end roller unit (34 a) and an intermediate roller unit (34 b), wherein a plurality of the bearing units (34 a to 34 c) are positioned such that the intermediate roller unit (34 b) is positioned between the first end roller unit (34 a) and the second end (23) of the slat track (17) with respect to the track longitudinal axis (19), It is characterized in that the method comprises the steps of, The slat track (17) and the roller bearing (27) are configured such that in the retracted position (11) and the first extended position (13) the slat (7) rests against the main wing (5), and in the second extended position (15) a gap (37) is formed between the trailing edge of the slat (7) and the leading edge of the main wing (5).
  2. 2. The wing (3) according to claim 1, wherein a plurality of the support units (34 a to 34 c) further comprises a second end support unit (34 c), wherein a plurality of the support units (34 a to 34 c) are positioned such that the intermediate roller unit (34 b) is positioned between the first end roller unit (34 a) and the second end support unit (34 c) with respect to the track longitudinal axis (19).
  3. 3. The wing (3) according to claim 2, wherein the slat track (17) and the roller bearing arrangement (27) are configured such that in the retracted position (11) a main load is transferred between the slat track (17) and the roller bearing arrangement (27) via the first end roller unit (34 a) and the second end bearing unit (34 c), and in the first extended position (13) and the second extended position (15) a main load is transferred between the slat track (17) and the roller bearing arrangement (27) via the first end roller unit (34 a) and the intermediate roller unit (34 b).
  4. 4. A wing (3) according to claim 2 or 3, wherein the intermediate roller unit (34 b) is configured to disengage from the engagement surface (35) in the retracted position (11) such that a void gap (52) exists between the intermediate roller unit (34 b) and the engagement surface (35), and the first end roller unit (34 a) and the second end support unit (34 c) are configured to engage with the engagement surface (35) in the retracted position (11), and Wherein the second end support unit (34 c) is configured to disengage from the engagement surface (35) in the first and second extended positions (13, 15), and the intermediate roller unit (34 b) and the first end roller unit (34 a) are configured to engage with the engagement surface (35) in the first and second extended positions (13, 15).
  5. 5. The wing (3) according to any one of claims 2 to 4, wherein the engagement surface (35) is configured to simultaneously engage with the first end roller unit (34 a) and any one of the intermediate roller unit (34 b) and the second end support unit (34 c).
  6. 6. A wing (3) according to any one of claims 2 to 5, wherein the slat track (17) comprises a recessed portion (30), wherein the recessed portion (30) is configured to align with the intermediate roller unit (34 b) along the track longitudinal axis (19) in the retracted position (11) such that a contact force between the intermediate roller unit (34 b) and the engagement surface (35) of the slat track (17) is eliminated or reduced.
  7. 7. The wing (3) according to claim 6, wherein the recessed portion (30) defines a discontinuity in the engagement surface (35) to divide the engagement surface (35) into a first engagement surface (35 a) extending in a first direction parallel to the track longitudinal axis (19) and a second engagement surface (35 b) extending in a second direction parallel to the track longitudinal axis (19), wherein the first end roller unit (34 a) is configured to engage with the first engagement surface (35 a) and the intermediate roller unit (34 b) and the second end support unit (34 c) are configured to engage with the second engagement surface (35 b).
  8. 8. Wing (3) according to claim 6 or 7, wherein the recessed portion (30) comprises a gradual transition in the form of a ramp to the engagement surface (35).
  9. 9. The wing (3) according to any one of claims 2 to 8, wherein the second end support unit (34 c) comprises a roller unit.
  10. 10. The wing (3) according to any one of claims 1 to 9, wherein the slat track (17) comprises first and second inner directional engagement surfaces (35 a, 35 b) and/or first and second outer directional engagement surfaces (35 e, 35 f), the first inner directional engagement surface (35 a) facing towards the second inner directional engagement surface (35 b) and the first outer directional engagement surface (35 e) facing away from the second outer directional engagement surface (35 f), and wherein each of the first end roller unit (34 a), the intermediate roller unit (34 b) and the second end support unit (34 c) is configured to engage with at least one of the first and second inner directional engagement surfaces (35 a, 35 b) and the first and second outer directional engagement surfaces (35 e, 35 f).
  11. 11. The wing (3) according to any one of claims 1 to 10, wherein the engagement surface (35) comprises a plurality of surface sections having different radii of curvature, as seen along the track longitudinal axis (19).
  12. 12. The wing according to claim 11, wherein the engagement surface (35) comprises four surface sections (43, 45, 47, 49) with four separate radii of curvature, as seen along the track longitudinal axis, Wherein a first surface section (43) having a first radius of curvature is associated with a travel path of the first end roller unit (34 a) between the retracted position (11), the first extended position (13) and the second extended position (15), Wherein a second surface section (45) having a second radius of curvature is associated with the recess (30), the recess (30) being aligned with the intermediate roller unit (34 b) in the retracted position (11) such that a contact force between the intermediate roller unit (34 b) and the engagement surface (35) of the slat track (17) is eliminated or reduced, Wherein a third surface section (47) having a third radius of curvature is associated with a travel path of the intermediate roller unit (34 b) between the retracted position (11), the first extended position (13) and the second extended position (15), and Wherein a fourth surface section (49) having a fourth radius of curvature is associated with a section for engagement with the second end support unit (34 c) in the retracted position (11).
  13. 13. The wing according to claim 11, wherein the engagement surface (35) comprises six surface sections (43, 45, 47, 49, 53, 55) with six individual radii of curvature, as seen along the track longitudinal axis, Wherein a first surface section (43) having a first radius of curvature is associated with a travel path of the first end roller unit (34 a) between the retracted position (11) and the first extended position (13), Wherein a second surface section (45) having a second radius of curvature is associated with the travel path of the first end roller unit (34 a) between the first extended position (13) and the second extended position (15), Wherein a third surface section (47) having a third radius of curvature is associated with the recess (30), in the retracted position (11) the recess (30) is aligned with the intermediate roller unit (34 b) such that a contact force between the intermediate roller unit (34 b) and the engagement surface (35) of the slat track (17) is eliminated or reduced, Wherein a fourth surface section (49) having a fourth radius of curvature is associated with a travel path of the intermediate roller unit (34 b) between the retracted position (11) and the first extended position (13), Wherein a fifth surface section (53) having a fifth radius of curvature is associated with a travel path of the intermediate roller unit (34 b) between the first extended position (13) and the second extended position (15), and Wherein a sixth surface section (55) having a sixth radius of curvature is associated with a section for engagement with the second end support unit (34 c) in the retracted position (11).
  14. 14. A leading edge high lift assembly (6), the leading edge high lift assembly (6) for an airfoil (3) according to any of claims 1 to 13, the leading edge high lift assembly (6) comprising: slat (7), and -A connection assembly (9), the connection assembly (9) being configured for movably connecting the slat (7) to the main wing (5) such that the slat (7) is movable between the retracted position (11), the first extended position (13) and the second extended position (15), Wherein the connection assembly (9) comprises a slat track (17), the slat track (17) extending along a track longitudinal axis (19) between a first end (21) and a second end (23) and having an intermediate portion (25) between the first end (21) and the second end (23), Wherein the first end (21) and/or the intermediate portion of the slat track (17) is configurable to be mounted to the slat (7), Wherein the slat track (17) is configurable to be mounted to the main wing (5) by roller bearing means (27) such that the slat track (17) is movable along the track longitudinal axis (19), Wherein the roller bearing arrangement (27) comprises a plurality of bearing units (34 a to 34 c), each of the bearing units (34 a to 34 c) being configurable to be mounted to the main wing (5) and having a bearing surface (22), the bearing surface (22) being configurable to engage with an engagement surface (35) provided to the slat track (17), and Wherein a plurality of the bearing units (34 a to 34 c) comprises at least a first end roller unit (34 a) and an intermediate roller unit (34 b), wherein a plurality of the bearing units (34 a to 34 c) are positioned such that the intermediate roller unit (34 b) is positioned between the first end roller unit (34 a) and the second end (23) of the slat track (17) with respect to the track longitudinal axis (19), It is characterized in that the method comprises the steps of, The slat track (17) and/or the roller bearing (27) are configured such that in the retracted position (11) and the first extended position (13) the slat (7) rests against the main wing (5), and in the second extended position (15) a gap (37) is formed between the trailing edge of the slat (7) and the leading edge of the main wing (5).
  15. 15. An aircraft (1) comprising a wing (3) according to any one of claims 1 to 13 and/or comprising a leading edge high lift assembly (6) according to claim 14.

Description

Wing, leading edge high lift assembly for an aircraft and aircraft Technical Field The present invention relates to a wing for an aircraft. Other aspects of the invention relate to leading edge high lift assemblies for such wings and aircraft including such wings and/or including such leading edge high lift assemblies. Background The described wing for an aircraft comprises a main wing and a leading edge high lift assembly comprising a slat and a connection assembly movably connecting the slat to the main wing such that the slat is movable relative to the main wing between a retracted position and several extended positions, in particular a first extended position and a second extended position. The first extended position is preferably associated with a partially extended position assumed during takeoff of the respective aircraft, while the second extended position is preferably associated with a fully extended position assumed during approach and landing of the respective aircraft. The connection assembly includes an elongated slat track extending along a track longitudinal axis between a first end and a second end, and having a mid-portion located between the first end and the second end. The slat track may have a curved form or a straight form along the track longitudinal axis. At least one or both of the first end and the intermediate portion of the slat track is mounted to the slat. The first end preferably corresponds to a front end of the connection assembly, for example an end that is positioned towards the intended direction of forward movement of the wing during flight of the aircraft. The first end of the slat track may preferably be mounted to the slat by any suitable means, for example by spherical bearing means, preferably in a fixed manner relative to the chord plane. As will be described, the slat track may preferably be mounted to the main wing by roller bearing means such that the slat track and the slat are movable relative to the main wing. The slat track may take the form of a C, for example, such that its surface opposes a circumferential surface of the roller bearing, wherein the distance between the upper and lower surfaces of the slat track is greater than the diameter of the roller bearing such that the roller bearing may engage only one of the upper or lower surfaces of the slat track at any one time. That is, the distance between the upper and lower surfaces of the slat track is selected such that a gap is provided between the roller bearing and either the upper or lower surface of the slat track such that the roller bearing cannot simultaneously engage and thereby wedge into the upper and lower surfaces of the slat track. The slat track is mounted to the main wing by roller support means such that the track is movable along a track longitudinal axis, in particular along a predetermined path, such as a stowed position when the slat is in a retracted position, a first deployed position when the slat is in a first extended position, and a second deployed position when the slat is in a second extended position. The load between the main wing and the slat track (e.g., almost all of the load, or perhaps the majority of the load or the main load) may be absorbed by the roller bearing device. The roller support device includes a plurality of support units mounted to the main wing and having support surfaces that engage engagement surfaces provided to the slat track. The plurality of support units includes at least a first end roller unit and an intermediate roller unit, wherein the plurality of support units are positioned such that the intermediate roller unit is positioned between the first end roller unit and the second end of the slat track relative to the track longitudinal axis, particularly when the slat is in the retracted position. The first end roller unit and/or the intermediate roller unit may be mounted to the main wing in any suitable manner, e.g. may be fixed or fastened to the main wing, e.g. may be bolted to the main wing. Similar airfoils are known in the art. Some known wings employ a sealed slat, the trailing edge of which is in contact with the leading edge of the main wing at all positions of the slat, so that there is never a gap between the trailing edge of the slat and the leading edge of the main wing. This avoids gaps, reduces aerodynamic drag and noise. Other wings have a slat with its trailing edge spaced from the leading edge of the main wing by a gap in all extended positions of the slat. Such a gap directs the fresh air flow from below the wing to the upper side of the wing, thereby inhibiting air flow separation and thus increasing lift. Disclosure of Invention It is therefore an object of the present invention to provide a wing whose aerodynamic performance versus noise generated by the extension of the slat is beneficial. This object is achieved in that the slat track and the roller bearing are configured such that in the retracted position and in the