Automated deployable fences for aircraft wings

Patent metadata

Field	Value
Publication number	US-11059564-B2
Application number	US-201816197927-A
Country	US
Kind code	B2
Filing date	Nov 21, 2018
Priority date	Nov 21, 2018
Publication date	Jul 13, 2021
Grant date	Jul 13, 2021

Abstract

Automated deployable fences for aircraft wings are described. An example apparatus includes a fence, a latching actuator, and a biasing actuator. The fence is coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel impedes a spanwise airflow along the wing when the fence is in the deployed position. The latching actuator is movable between a first position in which the latching actuator maintains the fence in the stowed position, and a second position in which the latching actuator releases the fence from the stowed position. The latching actuator moves from the first position to the second position in response to a control signal received at the latching actuator. The biasing actuator moves the fence from the stowed position to the deployed position in response to the latching actuator moving from the first position to the second position.

First claim

What is claimed is:

1. An apparatus comprising:
a fence coupled to a wing of an aircraft, the fence being movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin, the panel configured to impede a spanwise airflow along the wing when the fence is in the deployed position;
an electromechanical latch including a solenoid and an armature operatively coupled to the solenoid, the solenoid configured to cause the armature, in response to a control signal received at the electromechanical latch, to move from a first position in which the armature maintains the fence in the stowed position to a second position in which the armature releases the fence from the stowed position, the armature configured to:
engage a lip of the panel when the armature is in the first position and the fence is in the stowed position, wherein the engaging maintains the fence in the stowed position; and
disengage from the lip of the panel when the armature is in the second position, wherein the disengaging releases the fence from the stowed position and enables the fence to move from the stowed position to the deployed position; and

a biasing actuator configured to move the fence from the stowed position to the deployed position in response to the armature being moved from the first position to the second position.

2. The apparatus of claim 1 , wherein the electromechanical latch has a trapezoidal cross-sectional shape.

3. The apparatus of claim 1 , wherein the electromechanical latch is configured to receive the control signal from a controller of a flight control system of the aircraft, the flight control system including a sensor configured to detect an operational characteristic of the aircraft.

4. The apparatus of claim 3 , wherein the operational characteristic includes at least one of an airspeed, an angle of attack, or an airflow angle.

5. The apparatus of claim 3 , wherein the controller is configured to transmit the control signal to the electromechanical latch in response to the controller determining that the operational characteristic fails to satisfy a threshold.

6. The apparatus of claim 3 , wherein the flight control system includes a user interface configured to present data corresponding to the operational characteristic detected by the sensor, and wherein the controller is configured to transmit the control signal to the electromechanical latch in response to the controller receiving an actuation command from the user interface of the flight control system.

7. The apparatus of claim 1 , wherein the biasing actuator comprises a spring-loaded axle operatively coupled to the fence and mounted to the wing, the spring-loaded axle including an axle and a spring coiled around the axle, the axle having a central axis, the spring-loaded axle configured to move the fence from the stowed position to the deployed position.

8. The apparatus of claim 7 , wherein the central axis is substantially parallel to a chordwise direction of the wing, and wherein the panel extends in an inboard direction away from the central axis when the fence is in the stowed position.

9. The apparatus of claim 1 , wherein the biasing actuator comprises a living hinge extending between the panel of the fence and a base of the fence, the base being mounted to the wing, the base having a central axis, the living hinge configured to move the panel of the fence relative to the base of the fence and relative to the wing from the stowed position to the deployed position.

10. The apparatus of claim 9 , wherein the central axis is substantially parallel to a chordwise direction of the wing, and wherein the panel extends in an inboard direction away from the central axis when the fence is in the stowed position.

11. The apparatus of claim 1 , wherein the panel is recessed within the wing when the fence is in the stowed position.

12. A method for moving a fence coupled to a wing of an aircraft, the method comprising:
moving the fence between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin, the panel impeding a spanwise airflow along the wing when the fence is in the deployed position, the moving of the fence including:
moving an armature of an electromechanical latch, via a solenoid of the electromechanical latch operatively coupled to the armature, from (a) a first position in which the armature maintains the fence in the stowed position to (b) a second position in which the armature releases the fence from the stowed position, the moving of the armature being in response to a control signal received at the electromechanical latch, wherein the armature engages a lip of the panel when the armature is in the first position and the fence is in the stowed position, the engaging maintaining the fence in the stowed position, and wherein the armature disengages from the lip of the panel when the armature is in the second position, the disengaging releasing the fence from the stowed position and enables the fence to move from the stowed position to the deployed position; and
moving the fence from the stowed position to the deployed position via a biasing actuator in response to the moving of the armature from the first position to the second position.

13. The method of claim 12 , further comprising receiving the control signal at the electromechanical latch from a controller of a flight control system of the aircraft, the flight control system including a sensor configured to detect an operational characteristic of the aircraft.

14. The method of claim 13 , wherein the operational characteristic includes at least one of an airspeed, an angle of attack, or an airflow angle.

15. The method of claim 13 , further comprising transmitting the control signal from the controller to the electromechanical latch in response to the controller determining that the operational characteristic fails to satisfy a threshold.

16. The method of claim 13 , wherein the flight control system includes a user interface configured to present data corresponding to the operational characteristic detected by the sensor, and wherein the method further comprises transmitting the control signal from the controller to the electromechanical latch in response to the controller receiving an actuation command from the user interface of the flight control system.

17. The method of claim 12 , wherein the biasing actuator comprises a spring-loaded axle operatively coupled to the fence and mounted to the wing, the spring-loaded axle including an axle and a spring coiled around the axle, the axle having a central axis, the spring-loaded axle moving the fence from the stowed position to the deployed position in response to the moving of the armature from the first position to the second position.

18. The method of claim 17 , wherein the central axis is substantially parallel to a chordwise direction of the wing, and wherein the panel extends in an inboard direction away from the central axis when the fence is in the stowed position.

19. The method of claim 12 , wherein the biasing actuator comprises a living hinge extending between the panel of the fence and a base of the fence, the base being mounted to the wing, the base having a central axis, the living hinge moving the panel of the fence relative to the base of the fence and relative to the wing from the stowed position to the deplo

Assignees

• Boeing Co

Inventors

• Tillotson Brian
• Kettering Chris

Classifications

• B64C3/58 Primary

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

• B64C3/38 Primary

  Adjustment of complete wings or parts thereof · CPC title

• B64C5/10

  adjustable · CPC title

• Y02T50/10

  Drag reduction · CPC title

• B64C23/06 Primary

  by generating vortices · CPC title