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EP-4741284-A1 - WING FOR AN AIRCRAFT

EP4741284A1EP 4741284 A1EP4741284 A1EP 4741284A1EP-4741284-A1

Abstract

Disclosed is a wing (3) for an aircraft (1), comprising a main wing (5) and a leading edge high lift assembly (6) comprising a slat (7), and a 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 elongate slat track (17) that extends along a track longitudinal axis (19) between a first end (21) and a second end (23) and has an intermediate portion (25) between the first and second ends (21, 23), wherein the first end (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 a roller bearing (27) such that the slat track (17) is movable along the track longitudinal axis (19), wherein the roller bearing (27) comprises a plurality of bearing units (34a-c), each of the bearing units (34a-c) being mounted to the main wing (5) and having a bearing surface (22) for engaging an engagement surface (35) provided on the slat track (17), wherein the plurality of bearing units (34a-c) comprises at least a first end roller unit (34a) and an intermediate roller unit (34b), wherein the plurality of bearing units (34a-c) are positioned such that, relative to the track longitudinal axis (19), the intermediate roller unit (34b) is positioned between the first end roller unit (34a) and the second end (23) of the slat track (17). The object to provide a wing having a beneficial ratio of aerodynamic performance and noise generated by extension of the slat, is achieved in that the slat track (17) and the roller bearing (27) are configured such that in the retracted position (11) and in the first extended position (13), the slat (7) rests against the main wing (5), whereas 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).

Inventors

  • KREY, Dennis
  • SCHLIPF, BERNHARD

Assignees

  • Airbus Operations GmbH

Dates

Publication Date
20260513
Application Date
20251015

Claims (15)

  1. A wing (3) for an aircraft (1), comprising a main wing (5) and a leading edge high lift assembly (6) comprising a slat (7), and a 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 elongate slat track (17) that extends along a track longitudinal axis (19) between a first end (21) and a second end (23) and has an intermediate portion (25) between the first and second ends (21, 23), wherein the first end (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 a roller bearing (27) such that the slat track (17) is movable along the track longitudinal axis (19), wherein the roller bearing (27) comprises a plurality of bearing units (34a-c), each of the bearing units (34a-c) being mounted to the main wing (5) and having a bearing surface (22) for engaging an engagement surface (35) provided on the slat track (17), wherein the plurality of bearing units (34a-c) comprises at least a first end roller unit (34a) and an intermediate roller unit (34b), wherein the plurality of bearing units (34a-c) are positioned such that, relative to the track longitudinal axis (19), the intermediate roller unit (34b) is positioned between the first end roller unit (34a) and the second end (23) of the slat track (17), characterised in that the slat track (17) and the roller bearing (27) are configured such that in the retracted position (11) and in the first extended position (13), the slat (7) rests against the main wing (5), whereas 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. The wing (3) according to claim 1, wherein the plurality of bearing units (34a-c) further comprises a second end bearing unit (34c), wherein the plurality of bearing units (34a-c) are positioned such that, relative to the track longitudinal axis (19), the intermediate roller unit (34b) is positioned between the first end roller unit (34a) and the second end bearing unit (34c).
  3. The wing (3) according to claim 2, wherein the slat track (17) and the roller bearing (27) are configured such that in the retracted position (11) main loads are transferred between the slat track (17) and the roller bearing (27) via the first end roller unit (34a) and the second end bearing unit (34c), whereas in the first and second extended positions (13,15) main loads are transferred between the slat track (17) and the roller bearing (27) via the first end roller unit (34a) and the intermediate roller unit (34b).
  4. The wing (3) according to claim 2 or 3, wherein in the retracted position (11), the intermediate roller unit (34b) is configured to disengage with the engagement surface (35) such that a clearance gap (52) exists between the intermediate roller unit (34b) and the engagement surface (35), and the first end roller unit (34a) and the second end bearing unit (34c) are configured to engage the engagement surface (35); and wherein in the first and second extended positions (13, 15), the second end bearing unit (34c) is configured to disengage with the engagement surface (35) and the intermediate roller unit (34b) and the first end roller unit (34a) are configured to engage with the engagement surface (35).
  5. The wing (3) according to any of claims 2 to 4, wherein the engagement surface (35) is configured to be simultaneously engaged by the first end roller unit (34a) and either the intermediate roller unit (34) or the second end bearing unit (34c).
  6. The wing (3) according to any of claims 2 to 5, wherein the slat track (17, 217) comprises a recessed portion (30) wherein, in the retracted position (11), the recessed portion (30) is configured to align along the track longitudinal axis (19, 219) with the intermediate roller unit (34b) such that a contact force between the intermediate roller unit (34b) and the engagement surface (35) of the slat track (17, 217) is eliminated or reduced.
  7. The wing (3) according to claim 6, wherein the recessed portion (30) defines a discontinuity in the engagement surface (35) dividing the engagement surface (35) into a first engagement surface (35a) extending in a first direction parallel to the track longitudinal axis (19), and a second engagement surface (35b) extending in a second direction parallel to the track longitudinal axis (19), wherein the first end roller unit (34a) is configured to engage the first engagement surface (35a), and the intermediate roller unit (34b) and the second end bearing unit (34c) are configured to engage the second engagement surface (35b).
  8. The wing (3) according to claim 6 or 7, wherein the recessed portion (30) comprises a graduated transition to the engagement surface (35) in the form of a ramp.
  9. The wing (3) according to any of claims 2 to 8, wherein the second end bearing unit (34c) comprises a roller unit.
  10. The wing (3) according to any of claims 1 to 9, wherein the slat track (17) comprises a first and second internally oriented engagement surface (35a, 35b) and/or a first and second externally oriented engagement surface (35e, 35f), the first internally oriented engagement surface (35a) facing the second internally oriented engagement surface (35b), and the first externally oriented engagement surface (35e) facing away from the second externally oriented engagement surface (35f), and wherein each of the first end roller unit (34a), the intermediate roller unit (34b) and the second end bearing unit (34c) is configured to engage at least one of the first and second internally oriented engagement surface (35a, 35b) and the first and second externally oriented engagement surface (35e, 35f).
  11. The wing (3) according to any of claims 1 to 10, wherein the engagement surface (35), when viewed along the track longitudinal axis (19), comprises several surface sections with different curvature radii.
  12. The wing according to claim 11, wherein the engagement surface (35), when viewed along the track longitudinal axis, comprises four surface sections (43, 45, 47, 49) with four individual curvature radii, wherein a first surface section (43) with a first curvature radius relates to the travel path of the first end roller unit (34a) between the retracted position (11), the first extended position (13), and the second extended position (15), wherein a second surface section (45) with a second curvature radius relates to the recessed portion (30) that, in the retracted position (11), is aligned with the intermediate roller unit (34b) such that a contact force between the intermediate roller unit (34b) and the engagement surface (35) of the slat track (17, 217) is eliminated or reduced, wherein a third surface section (47) with a third curvature radius relates to the travel path of the intermediate roller unit (34b) between the retracted position (11), the first extended position (13), and the second extended position (15), and wherein a fourth surface section (49) with a fourth curvature radius relates to a section for engagement with the second end bearing unit (34c) in the retracted position (11).
  13. The wing according to claim 11, wherein the engagement surface (35), when viewed along the track longitudinal axis, comprises six surface sections (43, 45, 47, 49, 53, 55) with six individual curvature radii, wherein a first surface section (43) with a first curvature radius relates to the travel path of the first end roller unit (34a) between the retracted position (11) and the first extended position (13), wherein a second surface section (45) with a second curvature radius relates to the travel path of the first end roller unit (34a) between the first extended position (13) and the second extended position (15), wherein a third surface section (47) with a third curvature radius relates to the recessed portion (30) that, in the retracted position (11), is aligned with the intermediate roller unit (34b) such that a contact force between the intermediate roller unit (34b) and the engagement surface (35) of the slat track (17) is eliminated or reduced, wherein a fourth surface section (49) with a fourth curvature radius relates to the travel path of the intermediate roller unit (34b) between the retracted position (11) and the first extended position (13), wherein a fifth surface section (53) with a fifth curvature radius relates to the travel path of the intermediate roller unit (34b) between the first extended position (13) and the second extended position (15), and wherein a sixth surface section (55) with a sixth curvature radius relates to a section for engagement with the second end bearing unit (34c) in the retracted position (11).
  14. A leading edge high lift assembly (6) for the wing (3) according to any of claims 1 to 13, the leading edge high lift assembly 6) comprising a slat (7), and a connection assembly (9) configured for 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, and a second extended position (13, 15), wherein the connection assembly (9) comprises a slat track (17) that extends along a track longitudinal axis (19) between a first end (21) and a second end (23) and has an intermediate portion (25) between the first and second ends (21, 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 a roller bearing (27) such that the slat track (17) is movable along the track longitudinal axis (19), wherein the roller bearing (27) comprises a plurality of bearing units (34a-c), each of the bearing units (34a-c) being configurable to be mounted to the main wing (5) and having a bearing surface (22) configurable to engage an engagement surface (35) provided on the slat track (17), and wherein the plurality of bearing units (34a-c) comprises at least a first end roller unit (34a) and an intermediate roller unit (34b), wherein the plurality of bearing units (34a-c) are positioned such that, relative to the track longitudinal axis (19), the intermediate roller unit (34b) is positioned between the first end roller unit (34a) and the second end (23) of the slat track (17), characterized in that the slat track (17) and/or the roller bearing (27) are configurable such that in the retracted position (11) and in the first extended position (13), the slat (7) rests against the main wing (5), whereas 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. An aircraft (1) comprising a wing (3) according to any of claims 1 to 13, and/or comprising a leading edge high lift assembly (6) according to claim 14.

Description

The present invention relates to a wing for an aircraft. Further aspects of the invention relate to a leading edge high lift assembly for such a wing, as well as to an aircraft comprising such a wing and/or comprising such a leading edge high lift assembly. The described wing for an aircraft comprises a main wing and a leading edge high lift assembly, the 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 preferably relates to a partly extended position that is taken during take-off of the respective aircraft, while the second extended position preferably relates to a fully extended position that is taken during approach and landing of the respective aircraft. The connection assembly comprises an elongate slat track that extends along a track longitudinal axis between a first end and a second end and has an intermediate portion between the first and second ends. The slat track may have a curved or 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/are mounted to the slat. The first end preferably corresponds to a front end of the connection assembly, e.g. the end positioned towards the intended direction of forward motion of the wing during flight of an aircraft. The first end of the slat track may be preferably mounted to the slat by any appropriate means, e.g. by an arrangement of spherical bearings, preferably in a fixed manner with respect to a chord plane. The slat track may be preferably mounted to the main wing by a roller bearing, as will be described, such that the slat track and the slat are moveable relative to the main wing. The slat track may take the form of, for example, a C-shape, such that its surface lies opposite the circumferential surface of the roller bearing, wherein the distance between an upper surface and a lower surface of the slat track is larger than a diameter of a roller bearing, such that the roller bearing may engage only one of the upper surface or the lower surface of the slat track at any one time. I.e. the distance between the upper and lower surfaces of the slat track is selected such that a clearance is provided between the roller bearing and either the upper surface or the lower surface of the slat track, such that the roller bearing cannot engage with the upper and lower surfaces of the slat track at the same time, thereby becoming wedged therein. The slat track is mounted to the main wing by a roller bearing such that the track is movable along the track longitudinal axis, in particular along a predefined path, such as between a stowed position when the slat is in the retracted position, a first deployed position when the slat is in the first extended position, and a second deployed position when the slat is in the second extended position. The absorbing of the loads (e.g. substantially all the loads or the principal loads or main loads, which may be the majority of the loads) between the main wing and the slat track may be done by the roller bearing. The roller bearing comprises a plurality of bearing units that are mounted to the main wing and have a bearing surface that engages an engagement surface provided on the slat track. The plurality of bearing units comprises at least a first end roller unit and an intermediate roller unit, wherein the plurality of bearing units is positioned such that, relative to the track longitudinal axis, the intermediate roller unit is positioned between the first end roller unit and the second end of the slat track, in particular 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 appropriate way, for example may be fixed or fastened to the main wing, for example may be bolted to the main wing. Similar wings are known in the art. Some known wings employ sealed slats 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. Avoiding a gap reduced aerodynamic drag and noise. Other wings have slats the trailing edge of which is spaced from the leading edge of the main wing by a gap at all extended positions of the slat. Such a gap guides fresh air flow from underneath the wing to the upper side of the wing, thereby inhibiting flow separation and thus increasing lift. Therefore, the object of the present invention is to provide a wing having a beneficial ratio of aerodynamic performance and noise generated by extension of the slat. The object is achieved in that the slat track and the roller bearing are configured such th