Aircraft control mechanism

Patent metadata

Field	Value
Publication number	US-11242133-B2
Application number	US-201916692436-A
Country	US
Kind code	B2
Filing date	Nov 22, 2019
Priority date	Nov 26, 2018
Publication date	Feb 8, 2022
Grant date	Feb 8, 2022

Abstract

A control mechanism includes an existing aerodynamic device, such as a slat 5 , that moves between at least one deployed position and a retracted position; and a load-alleviation mechanism 10 arranged to move the aerodynamic device into a load-alleviation position in response to a load 18 , such as a gust of wind acting over a predetermined threshold. During flight, an aircraft can experience gusts of wind that cause strain on the wings 4 . The addition of a load-alleviation mechanism to a pre-existing aircraft component allows for gust loading to be alleviated without adding significantly to the weight or complexity of the aircraft. The control mechanism may be retro-fitted to existing aircraft.

First claim

The invention claimed is:

1. An aircraft control mechanism comprising:
an aerodynamic device configured to be attached to a wing main body of an aircraft;
a deployment mechanism selectively operable to move the aerodynamic device between at least one deployed position and a retracted position, and
a load-alleviation mechanism arranged to move the aerodynamic device into a load-alleviation position in response to a load acting on the aerodynamic device over a predetermined threshold,
wherein the load-alleviation mechanism, while a first position, is configured to position a trailing or leading edge of the aerodynamic device adjacent an upper surface of the wing main body while the aerodynamic device is in the retracted position,
wherein the load-alleviation mechanism, while in the load alleviation position, is configured to position the trailing or leading edge of the aerodynamic device apart from and above the upper surface while the aerodynamic device is in the retracted position, and
wherein the position of the trailing or leading edge of the aerodynamic device above the upper surface while the load-alleviation mechanism is in the load alleviation position spoils airflow over the upper surface of the wing main body.

2. The aircraft control mechanism as claimed in claim 1 , in which the aerodynamic device is configured to move into the load-alleviation position only when the aerodynamic device is in the retracted position.

3. The aircraft control mechanism as claimed in claim 1 , further comprising a spring arranged to apply a restoring force to bias the load-alleviation mechanism to the first position when the aerodynamic device is in the load-alleviation position.

4. The aircraft control mechanism as claimed in claim 1 , in which the aerodynamic device is connected to the deployment mechanism by the load-alleviation mechanism.

5. The aircraft control mechanism as claimed in claim 1 , in which the deployment mechanism comprises at least one track and a selectively operable actuator arranged to move the aerodynamic device along the track between the deployed and retracted positions.

6. The aircraft control mechanism as claimed in claim 1 , in which the load-alleviation mechanism includes a bistable mechanism, wherein the bistable mechanism has a first stable position corresponding to the first position of the load-alleviation mechanism, and a second stable position corresponding to the load alleviation position of the load-alleviation mechanism, and the bistable mechanism is biased to the first stable position.

7. The aircraft control mechanism as claimed in claim 6 , in which the bistable mechanism includes a ball detent device.

8. An aircraft wing comprising the wing main body and the aircraft control mechanism as claimed in claim 1 .

9. The aircraft wing as claimed in claim 8 , in which the wing main body comprises a leading edge and the aerodynamic device comprises a slat adjacent the leading edge.

10. The aircraft wing as claimed in claim 8 , in which the wing main body comprises a trailing edge and the aerodynamic device comprises a flap adjacent the trailing edge.

11. The aircraft wing as claimed in claim 8 , in which the aircraft control mechanism comprises at least one actuator arranged to move the aerodynamic device into and out of the load alleviation position.

12. The aircraft wing as claimed in claim 8 , wherein the wing main body include a leading edge and a trailing edge, and the aircraft control mechanism is a plurality of aircraft control mechanisms each of which includes a respective one of the aerodynamic device comprising a slat adjacent the leading edge or a flap adjacent the trailing edge.

13. The aircraft wing as claimed in claim 12 , in which the respective aircraft control mechanisms are arranged such that each aerodynamic device moves into its load-alleviation position at respective predetermined load thresholds.

14. An aircraft including the aircraft control mechanism as claimed in claim 1 .

15. An aircraft including the wing claimed in claim 8 .

16. An aircraft including the wing claimed in claim 11 , and further comprising a gust detector, and the actuator is arranged to move the aerodynamic device in response to signals from the gust detector.

17. An aircraft wing comprising:
a wing main body including a wing main body leading edge and a wing main body upper surface extending aft of the leading edge in a chordwise direction of the wing main body;
a track mounted to the wing main body and extending forward of the wing main body leading edge;
a slat mounted to the track and including a slat leading edge, a slat upper surface extending aft of the slat leading edge in the chordwise direction and a slat trailing edge at an aft portion of the slat upper surface, wherein the slat is configured to move by or along the track between a retracted position in which the slat is adjacent to and overlaps the wing main body leading edge and a portion of the wing main body upper surface; and a deployed position in which the slat protrudes forward of the wing main body leading edge in the chordwise direction such that a gap is formed between the slat and the wing main body leading edge and the wing main body upper surface; and
an extendable linkage mounted to the track and to the slat, wherein the extendable linkage is configured to pivot about the track to move the slat from the retracted position to a load-alleviation position by moving the trailing edge of the slat above and away of the wing main body upper surface while the slat leading edge remains adjacent the wing main body leading edge,
wherein airflow over the wing main body is spoiled by the trailing edge of the slat being above and away from the wing main body while the slat is in the load-alleviation position.

18. An aircraft wing comprising:
a wing main body including a wing main body leading edge and a wing main body upper surface extending aft of the leading edge in a chordwise direction of the wing main body;
a track mounted to the wing main body and extending forward of the wing main body leading edge;
a slat mounted to the track and including a slat leading edge, a slat upper surface extending aft of the slat leading edge in the chordwise direction and a slat trailing edge at an aft portion of the slat upper surface, wherein the slat is configured to move by or along the track between a retracted position in which the slat is adjacent to and overlaps the wing main body leading edge and a portion of the wing main body upper surface; and a deployed position in which the slat protrudes forward of the wing main body leading edge in the chordwise direction such that a gap is formed between the slat and the wing main body leading edge and the wing main body upper surface;
an extendable linkage mounted to the track and to the slat, wherein the extendable linkage is configured to pivot the slat from the retracted position to a load-alleviation position by moving the trailing edge of the slat above and away of the wing main body upper surface while the slat leading edge remains adjacent the wing main body leading edge, and
a spring mounted to the extendable linkage and biasing the extendable linkage in a retracted position which positions the slat trailing edge in the retracted position, wherein the extendable linkage is configured to move the slat to the load-alleviation position in response to an aerodynamic lift force applied to the slat which overcomes a biasing force of the spring.

19. The aircraft wing of claim 18 , further comprising a first pivot joint

Assignees

• Airbus Operations Ltd

Inventors

• Brakes David

Classifications

• B64C9/26 Primary

  by multiple flaps · CPC title

• B64C9/22

  at the front of the wing · CPC title

• B64C13/16 Primary

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C13/24

  Transmitting means · CPC title

• B64C9/02

  Mounting or supporting thereof · CPC title