High-lift trailing edge flap system for an aircraft wing unit

Patent metadata

Field	Value
Publication number	US-9545992-B2
Application number	US-201414499549-A
Country	US
Kind code	B2
Filing date	Sep 29, 2014
Priority date	Sep 30, 2013
Publication date	Jan 17, 2017
Grant date	Jan 17, 2017

Abstract

A high-lift trailing edge flap system for an aircraft wing unit is provided. In high-lift trailing edge flap system, the backward movement and the inclination of the trailing edge flap in the extended position are dissociated in order to allow for the incorporation of the actuating mechanism into the wing in the stowed position.

First claim

What is claimed is:

1. A high-lift flap system for a rear portion of an aircraft wing, the high-lift flap system comprising:
a trailing edge flap provided with a leading edge, a trailing edge, an upper surface and a lower surface, and
a mechanism for actuating said trailing edge flap, allowing said trailing edge flap to assume either a stowed position for which said trailing edge flap is housed at least in part in the rear portion of the aircraft wing, such that the upper surface and lower surface of said trailing edge flap are continuously aerodynamic with respect to the upper surface and lower surface of said rear portion of the aircraft wing and that the trailing edge of said trailing edge flap forms a portion of a trailing edge of said rear portion of the aircraft wing, or at least one extended position for which said trailing edge flap is set back from the trailing edge of said rear portion of the aircraft wing and inclined relative to the rear portion of the aircraft wing, said mechanism for actuating said trailing edge flap including:
one or more translation drive devices, which are housed at least in part in the rear portion of the aircraft wing and which comprise at least one driven movable element; and
one or more rotation devices, which are housed in said trailing edge flap and are connected to the at least one driven movable element so as to be able to rotate said trailing edge flap relative to the at least one driven movable element, about an axis parallel to the leading edge of said trailing edge flap,

wherein said rotation devices are formed by a rotating actuator, and the axis of rotation of said trailing edge flap corresponds to a rotation shaft of the rotation actuator.

2. The high-lift flap system according to claim 1 , wherein the rotating actuator is of the electro-hydraulic (EHA) type.

3. The high-lift flap system according to claim 1 , wherein said rotating actuator is arranged in the trailing edge flap in such a way that the axis of rotation of said trailing edge flap is located at a distance from the leading edge of the trailing edge flap between 30% and 40% of the chord length of said trailing edge flap.

4. The high-lift flap system according to claim 1 , wherein said rotating actuator and the at least one driven movable element are joined by a lug which is connected for conjoint rotation to the rotation shaft of said rotating actuator and engaged in a recess in said at least one driven movable element.

5. The high-lift flap system according to claim 1 , wherein said rotating actuator is arranged in a removable casing inserted in a corresponding housing of said trailing edge flap.

6. The high-lift flap system according to claim 5 , wherein said removable casing contributes to the structural resistance of said trailing edge flap when said removable casing is inserted and fixed in said housing.

7. The high-lift flap system according to claim 5 , wherein said housing is accessible via an opening made in the upper surface of said trailing edge flap, and a top face of said removable casing is formed in order to, when said removable casing is in place in the housing, seal said opening and form the corresponding portion of said upper surface of said trailing edge flap.

8. The high-lift flap system according to claim 1 , wherein said at least one driven movable element of the translation drive devices comprises at least one curved rail, which is guided and driven by drive wheels.

9. The high-lift flap system according to claim 8 , wherein said curved rail has an I-shaped cross section.

10. An aircraft, comprising:
at least one high-lift flap system having a trailing edge flap provided with a leading edge, a trailing edge, an upper surface and a lower surface, and a mechanism for actuating said trailing edge flap, allowing said trailing edge flap to assume either a stowed position for which said trailing edge flap is housed at least in part in the rear portion of the aircraft wing or at least one extended position for which said trailing edge flap is set back from a trailing edge of said rear portion of the aircraft wing and inclined relative to the rear portion of the aircraft wing, said mechanism for actuating said trailing edge flap including:
one or more translation drive devices, which are housed at least in part in the rear portion of the aircraft wing and which comprise at least one driven movable element; and
one or more rotation devices, which are housed in said trailing edge flap and are connected to the at least one driven movable element so as to be able to rotate said trailing edge flap relative to the at least one driven movable element, about an axis parallel to the leading edge of said trailing edge flap,
wherein said rotation devices are formed by a rotating actuator, and the axis of rotation of said trailing edge flap corresponds to a rotation shaft of the rotation actuator.

11. The high-lift flap system according to claim 1 , wherein said rotating actuator is arranged in the trailing edge flap in such a way that the axis of rotation of said trailing edge flap is located at a distance from the leading edge of the trailing edge flap at approximately 35% of the chord length of said trailing edge flap.

12. The aircraft according to claim 10 , wherein the rotating actuator is of the electro-hydraulic (EHA) type.

13. The aircraft according to claim 10 , wherein said rotating actuator is arranged in the trailing edge flap in such a way that the axis of rotation of said trailing edge flap is located at a distance from the leading edge of the trailing edge flap between 30% and 40% of the chord length of said trailing edge flap.

14. The aircraft according to claim 10 , wherein said rotating actuator and the at least one driven movable element are joined by a lug which is connected for conjoint rotation to the rotation shaft of said rotating actuator and engaged in a recess in said at least one driven movable element.

15. The aircraft according to claim 10 , wherein said rotating actuator is arranged in a removable casing inserted in a corresponding housing of said trailing edge flap.

16. The aircraft according to claim 15 , wherein said removable casing contributes to the structural resistance of said trailing edge flap when said removable casing is inserted and fixed in said housing.

17. The aircraft according to claim 15 , wherein said housing is accessible via an opening made in the upper surface of said trailing edge flap, and a top face of said removable casing is formed in order to, when said removable casing is in place in the housing, seal said opening and form the corresponding portion of said upper surface of said trailing edge flap.

18. The aircraft according to claim 10 , wherein said at least one driven movable element of the translation drive devices comprises at least one curved rail, which is guided and driven by drive wheels.

19. The aircraft according to claim 18 , wherein said curved rail has an I-shaped cross section.

Assignees

• Airbus Operations Sas
• Airbus Operations Sas

Inventors

• Guering Bernard

Classifications

• B64C13/40

  using fluid pressure · CPC title

• B64C2013/506

  Operations & Transport · mapped topic

• B64C13/50

  using electrical energy · CPC title

• Y02T50/32

  Cross-Sectional Technologies · mapped topic

• B64C13/28

  mechanical · CPC title