Deployable aerodynamic devices with reduced actuator loads, and related systems and methods

• US 7,954,769 B2
• Filed: 12/10/2007
• Issued: 06/07/2011
• Est. Priority Date: 12/10/2007
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Bushnell, Glenn S.
• Primary Examiner(s): Michener; Joshua J
• Application Number:
  US11/953,672
• Publication Number:
  US 20090146000A1
• Time in Patent Office: 1,275 Days
• Field of Search: 244/198, 244/201, 244/204, 244/204.1, 244/206, 244/212, 244213-215, 244/217, 244/76.A, 244 87- 90 A, 244/99.12, 244/99.13, 244/99.14, 244/99.2, 244/99.3, 244/234, 244/113, 244/110.D
• US Class Current: 244/213
• CPC Class Codes: B64C 13/38 with power amplification
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof
• CPC Class Codes: B64C 9/10 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 Class Codes: B64C 9/32 Air braking surfaces
• CPC Class Codes: B64C 9/323 associated with wings
• CPC Class Codes: B64C 9/34 collapsing or retracting against or within other surfaces or other members
• CPC Class Codes: Y02T 50/30 Wing lift efficiency
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

Deployable aerodynamic devices with reduced actuator loads, and related systems and methods are disclosed. An external flow system in accordance with a particular embodiment includes an external flow body, a deployable device carried by and movable relative to the external flow body, and a coupling connected between the external flow body and the deployable device. The system can further include an actuator device operatively coupled between the external flow body and the deployable device, with the actuator device positioned to move the deployable device along a motion path between a stowed position and the deployed position. The motion path can have a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position.

Claims

1. An aircraft system, comprising:

a lifting body;

a deployable aerodynamic device carried by and movable relative to the lifting body, the aerodynamic device including a first component pivotably coupled to the lifting body at a first location, and a second component translatably coupled to the lifting body at a second location, the first and second components being pivotably connected to each other at a third location; and

an actuator device coupled to the aerodynamic device and positioned to move the aerodynamic device relative to the lifting body along a motion path between a stowed position and a deployed position, the aerodynamic device being exposed to an adjacent airstream when in the deployed position; and

wherein the first component includes a first panel, the second component includes a second panel, and the actuator device includes at least one actuator coupled between the lifting body and the first panel at the first location to rotate the first panel relative to the lifting body, causing the second panel to translate along a guide path and rotate relative to the lifting body.

2. The aircraft system of claim 1 wherein the motion path has a first portion over which the load put out by the actuator device increases as the aerodynamic device moves toward the deployed position, and a second portion over which the load put out by the actuator device decreases as the aerodynamic device moves toward the deployed position.

3. The aircraft system of claim 1 wherein the first and second components are both exposed to the adjacent airstream around the lifting body when the aerodynamic device is in the deployed position.

4. The aircraft system of claim 1 wherein the deployed position is one of multiple deployed positions.

5. The aircraft system of claim 1 wherein the at least one actuator includes at least one rotary actuator.

6. The system of claim 5 wherein a first edge of the first panel is hingedly connected to a second edge of the second panel at the third location.

7. The system of claim 1 wherein the first component includes spaced-apart first and third panels, and wherein the second panel is positioned between the first and third panels, and wherein the first, second and third panels rotate in the same direction relative to the lifting body as the aerodynamic device moves from the stowed position to the deployed position.

8. The aircraft system of claim 1, further comprising a resilient element positioned to oppose motion of the aerodynamic device toward the deployed position.

9. The aircraft system of claim 1 wherein the lifting body includes a wing, and wherein the aerodynamic device includes a trailing edge device carried by the wing.

10. The aircraft system of claim 1 wherein the lifting body includes a helicopter rotor blade.

11. The aircraft system of claim 1 wherein the second component slides relative to the lifting body along a curved guide path.

12. An external flow system, comprising:

an external flow body;

a deployable device carried by and movable relative to the external flow body, the deployable device including a first component pivotably coupled to the lifting body at a first location, and a second component translatably coupled to the lifting body at a second location, the first and second components being pivotably connected to each other at a third location; and

an actuator device operatively coupled between the external flow body and the deployable device, the actuator device being positioned to move the deployable device along a motion path between a stowed position and a deployed position, the motion path having a first portion over which the load delivered by the actuator device increases as the deployed device moves toward the deployed position, and a second portion over which the load delivered by the actuator device decreases as the deployed device moves toward the deployed position, the first portion being between the stowed position and the second portion, wherein the first component includes a first panel, the second component includes a second panel, and the actuator device includes at least one actuator coupled between the lifting body and the first panel at the first location to rotate the first panel relative to the lifting body, causing the second panel to translate along a guide path and rotate relative to the lifting body.

13. The system of claim 12 wherein the deployed position is one of multiple deployed positions, and wherein actuator device provides a peak load at a point along the motion path between the stowed position and the deployed position furthest from the stowed position.

14. The system of claim 12, further comprising a resilient member coupled between the deployable device and the external flow body and applying a force on the deployable device tending to force the deployable device toward the stowed position.

15. The system of claim 12 wherein the external flow body includes an airfoil, and wherein the deployable device includes an aerodynamic device exposed to an adjacent airflow when in the deployed position.

16. A method for operating an aircraft system, comprising:

moving an aerodynamic device, carried by a lifting body, away from a stowed position and toward a deployed position, wherein the aerodynamic device includes a first component pivotably coupled to the lifting body at a first location, and a second component translatably coupled to the lifting body at a second location, the first and second components being pivotably connected to each other at a third location, the first component including a first panel and the second component including a second panel, and wherein moving the aerodynamic device includes actuating at least one actuator device coupled between the lifting body and the first panel at the first location to rotate the first panel and cause the second panel to translate along a guide path and rotate relative to the lifting body.

17. The method of claim 16 wherein rotating the first panel includes increasing a relative angle between the second component and the lifting body while decreasing a relative angle between the second component and the first component.

18. The method of claim 16 wherein moving the aerodynamic device away from the stowed position includes moving the aerodynamic device against a force provided by a resilient member coupled to the aerodynamic device.

19. The method of claim 16 wherein moving the aerodynamic device toward the deployed position includes:

moving the aerodynamic device over a first range of motion by increasing an output provided by the actuator device, while an external aerodynamic force on the aerodynamic device opposing the motion increases; and

moving the aerodynamic device over a second range of motion beyond the first range of motion while decreasing the output provided by the actuator device as the external aerodynamic force opposing the motion of the aerodynamic device toward the deployed position decreases.