Actuator arrangement for a wing assembly of an aircraft

Patent metadata

Field	Value
Publication number	US-12286228-B2
Application number	US-202318325944-A
Country	US
Kind code	B2
Filing date	May 30, 2023
Priority date	May 31, 2022
Publication date	Apr 29, 2025
Grant date	Apr 29, 2025

Abstract

A actuator arrangement is disclosed in which the high-lift device support that supports and guides movement of a high-lift device, such as a flap, is in axial alignment with a control actuator assembly that controls one or more control surfaces. This allows a single support fairing to be sufficient for covering both the track member and the control actuator assembly and allowing for reduced drag and weight.

First claim

The invention claimed is:

1. An actuator arrangement for a wing assembly of an aircraft, comprising:
a high-lift device support that movably supports a high-lift device such that the high-lift device is movable between a fully retracted position and a fully extended position;
at least one control surface movably supported at a trailing edge of the high-lift device; and,
at least one control actuator assembly operatively coupled to the control surface for controlling the deflection of the control surface,
wherein the control actuator assembly is mounted to the high-lift device support such that the control actuator assembly and the high-lift device support are aligned along a longitudinal direction.

2. The actuator arrangement according to claim 1 , wherein the control actuator assembly is arranged on the same side of the high-lift device as the high-lift device support in the installed position.

3. The actuator arrangement according to claim 1 , wherein the control actuator assembly is arranged aft of the high-lift device support in the installed position.

4. The actuator arrangement according to claim 1 , wherein the control actuator assembly is mounted to the high-lift device so as to be movable together with the high-lift device.

5. The actuator arrangement according to claim 1 , wherein the control actuator assembly is mechanically coupled to the control surface via a transmission member.

6. The actuator arrangement according to claim 1 , wherein the control actuator assembly includes a rotatory actuator that has a rotatable lever member that is operatively coupled via a transmission member, to the control surface.

7. The actuator arrangement according to claim 6 , wherein the transmission member is mechanically coupled to the control actuator assembly and/or the control surface and/or the rotatable lever member via a trunnion.

8. The actuator arrangement according to claim 1 , wherein the high-lift device support comprises a support fairing that extends along the longitudinal direction of the high-lift device support, wherein the support fairing covers the control actuator assembly such that at least in the fully retracted position, the control actuator assembly is at least partially, covered by the support fairing.

9. The actuator arrangement according to claim 1 , wherein the at least one control surface comprises a first control surface and a second control surface, wherein the control actuator assembly comprises a first control actuator and a second control actuator that are operatively coupled to the first control surface and to the second control surface via a first transmission member and second transmission member, respectively, for individually controlling the deflection of the first and second control surfaces.

10. The actuator arrangement according to claim 9 , wherein the first control actuator or the second control actuator includes an offset member that is configured such that the first and second transmission members do not mechanically block each other.

11. The actuator arrangement according to claim 1 , wherein the high-lift device support comprises a track member that is configured to support and guide the high-lift device along a movement path between the fully retracted position and the fully extended position.

12. The actuator arrangement according to claim 1 , wherein the high-lift device comprises a bracket member that engages the high-lift device support.

13. The actuator arrangement according to claim 1 , further comprising a deployment actuator that is configured to drive the high-lift device from the fully retracted position to the fully extended position and vice versa.

14. A wing assembly for an aircraft comprising a wing box and the installed actuator arrangement according to claim 1 .

15. An aircraft comprising the actuator arrangement according to claim 1 .

16. An aircraft comprising the wing assembly according to claim 14 .

17. The actuator arrangement according to claim 1 , wherein the control actuator assembly is fully covered by a support fairing.

18. The actuator arrangement according to claim 1 , wherein the high-lift device comprises a bracket member that engages a track member.

19. An actuator arrangement for a wing assembly of an aircraft, comprising:
a high-lift device support that movably supports a high-lift device such that the high-lift device is movable between a fully retracted position and a fully extended position;
at least one control surface that is movably supported by the high-lift device; and,
at least one control actuator assembly operatively coupled to the control surface for controlling the deflection of the control surface,
wherein the control actuator assembly is mounted to the high-lift device by a cantilever member such that the control actuator assembly and the high-lift device support are aligned along a longitudinal direction, and
wherein the high-lift device support comprises a track member.

Assignees

• Airbus Operations Gmbh

Inventors

• Andreani Luc
• Lorenz Florian

Classifications

• B64C9/16

  at the rear of the wing · CPC title

• B64C9/18

  by single flaps · CPC title

• B64C2009/005

  Ailerons · CPC title

• B64C9/34

  collapsing or retracting against or within other surfaces or other members · CPC title

• B64C9/14

  forming slots · CPC title