Aerodynamic system for an aircraft

Patent metadata

Field	Value
Publication number	US-12371148-B2
Application number	US-202418630256-A
Country	US
Kind code	B2
Filing date	Apr 9, 2024
Priority date	Apr 11, 2023
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

An aerodynamic system for an aircraft. The aerodynamic system includes a first aerodynamic component configured to be movably coupled to a primary structure of the aircraft, a second aerodynamic component which is movably coupled to the first aerodynamic component and a first panel element coupled to the first aerodynamic component. The first panel element at least partially covers a gap between the first aerodynamic component and the second aerodynamic component. The aerodynamic system further includes a sealing element arranged between the first aerodynamic component and the second aerodynamic component. The sealing element is configured to at least partially block an airflow between the first aerodynamic component and the second aerodynamic component.

First claim

The invention claimed is:

1. An aerodynamic system for an aircraft, comprising:
a first aerodynamic component configured to be movably coupled to a primary structure of the aircraft;
a second aerodynamic component which is movably coupled to the first aerodynamic component;
a first panel element coupled to the first aerodynamic component, wherein the first panel element at least partially covers a gap between the first aerodynamic component and the second aerodynamic component;
a sealing element arranged between the first aerodynamic component and the second aerodynamic component, wherein the sealing element is configured to at least partially block an airflow between the first aerodynamic component and the second aerodynamic component,
wherein the sealing element is arranged between a nose section of the second aerodynamic component and a trailing edge section of the first aerodynamic component;
wherein the second aerodynamic component comprises a recess at the nose section of the second aerodynamic component;
wherein the aerodynamic system further comprises a nose support element which is received within the recess at the nose section of the second aerodynamic component; and
wherein the sealing element is arranged between the nose support element of the second aerodynamic component and the trailing edge section of the first aerodynamic component.

2. The aerodynamic system of claim 1 , wherein the sealing element is spatially separated from the first panel element.

3. The aerodynamic system according to claim 1 ,
wherein the trailing edge section of the first aerodynamic component comprises a trailing edge support unit; and
wherein the trailing edge support unit is configured to support a portion of the first panel element.

4. The aerodynamic system according to claim 3 , wherein the sealing element is arranged between the nose section of the second aerodynamic component and the trailing edge support unit of the first aerodynamic component.

5. The aerodynamic system according to claim 1 ,
wherein the second aerodynamic component is pivotably coupled to the first aerodynamic component, thereby enabling a pivotal movement of the second aerodynamic component with respect to the first aerodynamic component; and
wherein the sealing element is in contact with the trailing edge section of the first aerodynamic component and the nose section of the second aerodynamic component during the pivotal movement of the second aerodynamic component with respect to the first aerodynamic component.

6. The aerodynamic system according to claim 1 , wherein the sealing element is configured to be pressed against the trailing edge section of the first aerodynamic component thereby blocking the airflow between the first aerodynamic component and the second aerodynamic component.

7. The aerodynamic system according to claim 1 , wherein the sealing element is configured to be pressed against the nose section of the second aerodynamic component thereby blocking the airflow between the first aerodynamic component and the second aerodynamic component.

8. The aerodynamic system according to claim 1 , wherein the sealing element is a D-type sealing element.

9. The aerodynamic system according to claim 1 , wherein the sealing element is a blade-type sealing element.

10. The aerodynamic system according to claim 1 ,
wherein the first aerodynamic component has an aerodynamic outer surface and the second aerodynamic component has an aerodynamic outer surface; and
wherein the first panel element at least partially covers a gap between the aerodynamic outer surface of the first aerodynamic component and the aerodynamic outer surface of the second aerodynamic component.

11. The aerodynamic system according to claim 10 , wherein the first panel element has a flexible portion that is configured to establish a contact with the aerodynamic outer surface of the second aerodynamic component.

12. The aerodynamic system according to claim 1 , further comprising:
a second panel element coupled to the first aerodynamic component,
wherein the second panel element at least partially covers a gap between the first aerodynamic component and the second aerodynamic component.

13. The aerodynamic system according to claim 12 ,
wherein the sealing element is spatially separated from the second panel element; and
wherein the sealing element is arranged between the first panel element and the second panel element.

14. The aerodynamic system according to claim 1 ,
wherein the aerodynamic system is a trailing edge system;
wherein the first aerodynamic component is a first trailing edge movable; and
wherein the second aerodynamic component is a second trailing edge movable.

15. An aircraft comprising:
a wing structure;
the aerodynamic system according to claim 1 ;
wherein the second aerodynamic component is movably coupled to the wing structure via the first aerodynamic component.

Assignees

• Airbus Operations Gmbh

Inventors

• Daandels Dort
• Lorenz Florian
• Wunderlich Sönke

Classifications

• B64C9/10

  one surface adjusted by movement of another, e.g. servo tabs (B64C9/04 takes precedence; adjusting surfaces of different type or function B64C9/12) · CPC title

• B64C9/16

  at the rear of the wing · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C9/26

  by multiple flaps · CPC title

• B64C9/04 Primary

  with compound dependent movements · CPC title