Aircraft spoiler and actuation apparatus

Patent metadata

Field	Value
Publication number	US-11780564-B2
Application number	US-202117487798-A
Country	US
Kind code	B2
Filing date	Sep 28, 2021
Priority date	Nov 9, 2020
Publication date	Oct 10, 2023
Grant date	Oct 10, 2023

Abstract

A spoiler for an aircraft wing is movable between a stowed configuration and a deployed configuration in a “pop-up” manner. The spoiler includes a hinged top flap movable between a first position and a second position, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator. When the hinged top flap is in the second position, airflow over the top surface of the aircraft wing acts to pull the spoiler into the deployed position.

First claim

The invention claimed is:

1. An aircraft wing comprising:
a wing structure, and
a spoiler movable relative to the wing structure between a stowed configuration and a deployed configuration,
wherein the spoiler comprises a hinged top flap movable between a first position and a second position,
wherein the spoiler comprises a linear guide mechanism arranged to constrain movement of the spoiler to a direction perpendicular to an upper surface of the wing structure;
wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator,
wherein when the spoiler is in the stowed configuration the hinged top flap is in the first position, and
when the spoiler is in the deployed position the hinged top flap is in the second position.

2. The aircraft wing as claimed in claim 1 , wherein in the stowed configuration, an upper surface of the hinged top flap is a continuation of the upper surface of the wing structure.

3. The aircraft wing as claimed in claim 2 , wherein there is a smooth transition from the wing structure to the spoiler when the spoiler is in the stowed configuration.

4. The aircraft wing as claimed in claim 1 , wherein the actuator is arranged to control movement of the hinged top flap between the first position and the second position.

5. The aircraft wing as claimed in claim 1 , wherein the actuator is arranged to secure the hinged top flap in the first position when the spoiler is in the stowed configuration.

6. The aircraft wing as claimed in claim 1 , wherein the actuator is arranged to allow movement of the hinged top flap into the second position prior to movement of the spoiler into the deployed position.

7. The aircraft wing as claimed in claim 1 , wherein when in the second position, the hinged top flap is arranged such that hinged top flap interrupts airflow over the aircraft wing.

8. The aircraft wing as claimed in claim 1 , wherein the spoiler is arranged such that as part of movement from the deployed position to the stowed position, the hinged top flap is moved into the first position prior to any retraction of the spoiler.

9. The aircraft wing as claimed in claim 1 , wherein movement of the hinged top flap into the first position opens an air gap in the spoiler.

10. The aircraft wing as claimed in claim 9 , where the spoiler is arranged such that when the hinged top flap is in the second position, an air dam closes an air gap which exists when the hinged top flap is in the first position.

11. The aircraft wing as claimed in claim 1 , wherein the actuator is arranged to move the spoiler from the deployed configuration to the stowed configuration.

12. The aircraft wing as claimed in claim 1 , wherein the actuator comprises a clutch arrangement which allows free movement in one direction when the spoiler is moved into the deployed configuration.

13. The aircraft wing as claimed in claim 12 , wherein the clutch arrangement is configured to engage a drive mechanism to allow the spoiler to be retracted into the stowed configuration.

14. The aircraft wing as claimed in claim 13 , wherein the clutch arrangement is arranged to be lockable to prevent movement of the hinged top flap between the first position and the second position.

15. The aircraft wing as claimed in claim 12 , wherein the clutch mechanism comprises a ramped dog clutch, a spring, and a series of friction clutch plates, and wherein the spring is between the ramped dog clutch and the series of friction clutch plates.

16. The aircraft wing as claimed in claim 1 , wherein the actuator comprises a cable and cable drum.

17. The aircraft wing as claimed in claim 16 , wherein the cable is attached at one end to the hinged top flap and at the other end to the cable drum, and the cable is held under tension when the spoiler is in the stowed position, to as to secure the hinged top flap in the first position.

18. The aircraft wing as claimed in claim 17 , wherein the tension in the cable is released to allow the hinged top flap to move into the second position, and to allow the spoiler to move into the deployed position unencumbered.

19. The aircraft wing as claimed in claim 18 , wherein in order to retract the spoiler, the cable is tensioned to pull the hinged top flap into the first position.

20. The aircraft wing as claimed in claim 19 , wherein the cable is arranged to be reeled around the cable drum in order to retract the spoiler into the stowed position.

21. A method of deploying a stowed spoiler in an aircraft wing, the aircraft wing comprising a wing structure and a spoiler movable relative to the wing structure between a stowed configuration and a deployed configuration, wherein the spoiler comprises a hinged top flap movable between a first position and a second position, wherein the spoiler comprises a linear guide mechanism arranged to constrain movement of the spoiler along a direction perpendicular to an upper surface of the wing structure, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator, wherein when the spoiler is in the stowed configuration the hinged top flap is in the first position, and when the spoiler is in the deployed position the hinged top flap is in the second position,
the method comprising:
disengaging the actuator such that the hinged top flap is unconstrained thereby allowing negative air-pressure to move the hinged top flap into the second position, the negative air-pressure acting on the spoiler such that the spoiler moves into the deployed position.

22. The method as claimed in claim 21 , wherein the actuator comprises a clutch mechanism, wherein the clutch mechanism is operable between an engaged mode in which the hinged top flap is constrained by the actuator, and a disengaged mode in which the hinged top flap is unconstrained by the actuator, and the method comprises the step of moving the clutch mechanism from the engaged mode to the disengaged mode.

23. A method of retracting a deployed spoiler in an aircraft wing, wherein the aircraft wing comprises a wing structure and a spoiler movable relative to the wing structure between a stowed configuration and a deployed configuration, wherein the spoiler comprises a hinged top flap movable between a first position and a second position, wherein the spoiler comprises a linear guide mechanism arranged to constrain movement of the spoiler along a direction perpendicular to an upper surface of the wing structure, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator, wherein when the spoiler is in the stowed configuration the hinged top flap is in the first position, and when the spoiler is in the deployed position the hinged top flap is in the second position, and
the method comprises:
engaging the actuator such that the hinged top flap is constrained by the actuator and moved into the first position.

24. A method of retracting a spoiler in an aircraft wing as claimed in claim 23 , wherein the actuator comprises a clutch mechanism operable between an engaged mode in which the hinged top flap is constrained by the actuator, and a disengaged mode in which the hinged top flap is unconstrained by the actuator, and the method comprises moving the clutch mechanism from the disengaged mode t

Assignees

• Airbus Operations Ltd

Inventors

• Bishop Benjamin
• Bryant Anthony

Classifications

• B64C13/30 Primary

  using cable, chain, or rod mechanisms · CPC title

• B64C9/26

  by multiple flaps · CPC title

• B64C13/34

  using toothed gearing · CPC title

• B64C3/58 Primary

  provided with fences or spoilers (adjustable for control purposes B64C9/00) · CPC title

• B64C9/323 Primary

  associated with wings · CPC title