Flap system for an aircraft and method of operating a flap fairing at an aircraft wing

Patent metadata

Field	Value
Publication number	US-12344377-B2
Application number	US-202418425093-A
Country	US
Kind code	B2
Filing date	Jan 29, 2024
Priority date	Jan 31, 2023
Publication date	Jul 1, 2025
Grant date	Jul 1, 2025

Abstract

A flap system for an aircraft comprises a wing structure, a trailing-edge and an attachment unit for movably coupling the trailing-edge movable to the wing structure. The attachment unit comprises an attachment mechanism and a cover element which at least partly encloses the attachment mechanism. The attachment unit comprises a drive element which is configured to move the cover element along an aerodynamic outer surface of a skin section of the wing structure between a first position and a second position, wherein the movement of the cover element along the aerodynamic outer surface is defined by a translational movement of the cover element relative to the skin section.

First claim

The invention claimed is:

1. A flap system for an aircraft comprising:
a wing structure having a skin section with an aerodynamic outer surface;
a trailing-edge unit comprising at least one trailing-edge movable configured to move between a retracted position and an extended position; and
an attachment unit for movably coupling the at least one trailing-edge movable to the wing structure;
wherein the attachment unit comprises an attachment mechanism and a cover element which at least partly encloses the attachment mechanism;
wherein the attachment unit further comprises a drive element configured to move the cover element along the aerodynamic outer surface of the skin section between a first position and a second position;
wherein a movement of the cover element along the aerodynamic outer surface of the skin section between the first position and the second position is defined by a translational movement of the cover element relative to the skin section between the first position and the second position.

2. The flap system according to claim 1 , wherein a rotational movement of at least a part of the cover element relative to the skin section is at least partially prevented when the cover element is moved along the aerodynamic outer surface of the skin section between the first position and the second position.

3. The flap system according to claim 1 , wherein the translational movement of the cover element relative to the skin section between the first position and the second position is defined by a movement of the cover element parallel to the skin section.

4. The flap system according to claim 1 , wherein the cover element covers the attachment mechanism from an air flow on the aerodynamic outer surface of the skin section when being moved along the aerodynamic outer surface of the skin section between the first position and the second position.

5. The flap system according to claim 1 , wherein the cover element comprises a first cover portion and a second cover portion, and
wherein the attachment unit is configured to couple the first cover portion to the wing structure and to couple the second cover portion to the wing structure, such that the second cover portion is movable relative to the first cover portion.

6. The flap system according to claim 1 , wherein the attachment mechanism of the attachment unit is configured to movably couple the at least one trailing-edge movable to the wing structure in order to enable a movement of the at least one trailing-edge movable between the retracted position and the extended position.

7. The flap system according to claim 1 , wherein the drive element is configured to move the at least one trailing-edge movable via the attachment mechanism, and
wherein the cover element is coupled to the attachment mechanism via a coupling element, such that the drive element is configured to move the cover element via the attachment mechanism.

8. The flap system according to claim 1 , wherein the drive element is configured to move the cover element along the aerodynamic outer surface of the skin section between the first position and the second position while the at least one trailing-edge movable is moved from the retracted position to the extended position.

9. The flap system according to claim 1 , further comprising:
a sealing element configured to seal a gap between the cover element and the aerodynamic outer surface of the skin section.

10. The flap system according to claim 9 , wherein the sealing element is configured to seal the gap between the cover element and the aerodynamic outer surface of the skin section during the movement of the cover element along the aerodynamic outer surface of the skin section between the first position and the second position.

11. The flap system according to claim 9 , wherein the attachment unit comprises an engagement mechanism for movably coupling the cover element to the wing structure, and
wherein the engagement mechanism comprises a track element and a corresponding engagement element that is configured to engage with the track element in order to movably couple the cover element to the wing structure.

12. The flap system according to claim 11 , wherein the track element is coupled to the cover element and the engagement element is coupled to the wing structure, or
wherein the track element is coupled to the wing structure and the engagement element is coupled to the cover element.

13. The flap system according to claim 11 , wherein the engagement element comprises a roller arrangement that is configured for rolling engagement with the track element.

14. A method of operating a flap fairing at an aircraft wing, the method comprising:
activating a drive element which is coupled to a wing structure of the aircraft wing, wherein the wing structure comprises a skin section with an aerodynamic outer surface;
moving, by the drive element, at least one trailing-edge movable coupled to the drive element via an attachment mechanism, such that the at least one trailing-edge movable is moved from a retracted position to an extended position; and,
moving, by the drive element, the flap fairing which at least partly encloses the attachment mechanism,
wherein moving the flap fairing comprises moving the flap fairing along the aerodynamic outer surface of the skin section between a first position and a second position, and
wherein a movement of the flap fairing between the first position and the second position is defined by a translational movement of the flap fairing relative to the skin section between the first position and the second position.

Assignees

• Airbus Operations Gmbh

Inventors

• Lorenz Florian
• Schlipf Bernhard

Classifications

• B64C13/28

  mechanical · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C9/34

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

• B64C9/32

  Air braking surfaces · CPC title

• B64C2009/143

  comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps · CPC title