System for driving a slat device of an aircraft wing

Patent metadata

Field	Value
Publication number	US-10618644-B2
Application number	US-201715584267-A
Country	US
Kind code	B2
Filing date	May 2, 2017
Priority date	May 3, 2016
Publication date	Apr 14, 2020
Grant date	Apr 14, 2020

Abstract

Disclosed herein is an exemplary embodiment of a system for driving a slat of an aircraft. The system includes first and second hinge support elements of a wing structure, a first arm device, a second arm device, and a third arm device. Also disclosed is an aircraft having the system, an aircraft wing having the system, and a method for driving a slat of an aircraft. The system utilizes a particular configuration of connection junctions, which rotatably connect the arm devices and the hinge support elements.

First claim

What is claimed is:

1. A system for driving slats of an aircraft, the system comprising:
a first hinge support element of an aircraft wing structure;
a second hinge support element of the aircraft wing structure;
a first arm device comprising a first connection junction, a second connection junction, and a third connection junction, the first arm device having a steady curved shape between the first connection junction and the second connection junction;
a second arm device comprising a first connection junction, a second connection junction, and a third connection junction; and
a third arm device comprising a first connection junction and a second connection unction;
wherein the first arm device is rotatably connected by the first connection junction of the first arm device to the first hinge support element, the second connection junction of the first arm device is configured to be rotatably connected to a rear portion of a slat, and the third connection junction of the first arm device is arranged between the first connection junction of the first arm device and the second connection junction of the first arm device;
wherein the second arm device is linearly extendable and rotatably connected by the first connection junction of the second arm device to the second hinge support element, the second connection junction of the second arm device is configured to be rotatably connected to a front portion of the slat, and the third connection junction of the second arm device is arranged between the first connection junction of the second arm device and the second connection junction of the second arm device; and
wherein the third arm device is rotatably connected by the first connection junction of the third arm device to the third connection junction of the first arm device, and the second connection junction of the third arm device is rotatably connected to the third connection junction of the second arm device.

2. The system according to claim 1 , wherein the first arm device comprises a J-shaped cross profile or an L-shaped cross profile.

3. The system according to claim 2 , wherein the second arm device comprises a first shaft element and a second shaft element, and wherein the first and second shaft elements are connected by a linear guide mechanism configured to provide a translational shift between the first and second shaft elements, such that the second arm device is translationally and/or linearly extendable.

4. The system according to claim 3 , wherein the first shaft element is rotatably connected by an associated first connection junction to the second hinge support element and comprises an associated third connection junction, and wherein the second shaft element comprises an associated second connection junction.

5. The system according to claim 1 , wherein the first arm device is rotatable about the first hinge support element at least between a first pivot position and a second pivot position, wherein in the first pivot position, the system is configured to arrange the slat in a retracted position within an aircraft wing, such that a forward leading edge of the slat is forward of a rear trailing edge of the slat.

6. The system according to claim 5 , wherein in the second pivot position of the first arm device, the system is configured to arrange the slat in an operation position outside the aircraft wing, such that the rear trailing edge of the slat is forward of a forward leading edge of the aircraft wing or is arranged above and in overlap with the forward leading edge of the aircraft wing.

7. The system according to claim 6 , wherein the system is configured to drive the slat from the retracted position to the operation position along a trajectory, such that the forward leading edge of the slat is constantly forward of the rear trailing edge of the slat.

8. The system according to claim 1 , wherein the first arm device comprises a fourth connection junction, wherein the system comprises a fourth arm device rotatably connected by an associated first connection junction to the fourth connection junction of the first arm device, and wherein the fourth arm device comprises a second connection junction configured to be rotatably connected to the bottom panel of the aircraft wing.

9. An aircraft comprising a system according to claim 1 .

10. An aircraft wing for an aircraft, comprising:
an aircraft wing structure;
a slat; and
a system comprising:
a first hinge support element of the aircraft wing structure;
a second hinge support element of the aircraft wing structure;
a first arm device comprising a first connection junction, a second connection junction, and a third connection junction, the first arm device having a steady curved shape between the first connection junction and the second connection junction;
a second arm device comprising a first connection junction, a second connection junction, and a third connection junction; and
a third arm device comprising a first connection junction and a second connection junction;

wherein the first arm device is rotatably connected by the first connection junction of the first arm device to the first hinge support element, the second connection junction of the first arm device is configured to be rotatably connected to a rear portion of the slat, and the third connection junction of the first arm device is arranged between the first connection junction of the first arm device and the second connection junction of the first arm device;
wherein the second arm device is linearly extendable and rotatably connected by the first connection junction of the second arm device to the second hinge support element, the second connection junction of the second arm device is configured to be rotatably connected to a front portion of the slat, and the third connection junction of the second arm device is arranged between the first connection junction of the second arm device and the second connection junction of the second arm device;
wherein the third arm device is rotatably connected by the first connection junction of the third arm device to the third connection junction of the first arm device, and the second connection junction of the third arm device is rotatably connected to the third connection junction of the second arm device;
wherein the first and second hinge support elements are arranged within the aircraft wing and attached to the aircraft wing structure;
wherein the second connection junction of the first arm device is rotatably connected to the rear portion of the slat; and
wherein the second connection junction of the second arm device is rotatably connected to a front portion of the slat.

11. The aircraft wing according to claim 10 , wherein the first hinge support element is arranged at a first internal, forward leading section of the aircraft wing structure, and wherein the second hinge support element is arranged rearward the first section of the aircraft wing structure at a second internal section of the aircraft wing structure.

12. The aircraft wing according to claim 10 , wherein the aircraft wing comprises a bottom panel, wherein the system is configured to move, in particular pivot, the bottom panel from a closed position to an open position before or while rotating the first arm device from the first pivot position to the second pivot position.

Assignees

• Airbus Operations Gmbh

Inventors

• Gemilang Atra Surya
• Hencke Marc

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

• B64C3/50 Primary

  by leading or trailing edge flaps · CPC title

• B64C13/30

  using cable, chain, or rod mechanisms · CPC title

• B64C9/24

  by single flap · CPC title

• B64C9/26

  by multiple flaps · CPC title