SLIDABLE DIVERGENT TRAILING EDGE DEVICE

• US 20150353188A1
• Filed: 06/06/2014
• Published: 12/10/2015
• Est. Priority Date: 06/06/2014
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Jamison, Flint M., Amorosi, Stephen R., Klein, Michael K.
• Granted Patent: US 9,463,869 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 13/24 Transmitting means
• CPC Class Codes: B64C 2003/147 comprising trailing edges of particular shape
• CPC Class Codes: B64C 3/28 Leading or trailing edges attached to primary structures, e.g. forming fixed slots
• CPC Class Codes: B64C 3/38 Adjustment of complete wings or parts thereof
• CPC Class Codes: B64C 3/50 by leading or trailing edge flaps
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof
• CPC Class Codes: B64C 9/16 at the rear of the wing
• CPC Class Codes: Y02T 50/10 Drag reduction
• CPC Class Codes: Y02T 50/30 Wing lift efficiency
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

A wing includes a trailing edge, and a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position. The trailing edge device is located entirely within the trailing edge when stowed, and it increases lift over drag of the wing when deployed.

Claims

1. A wing comprising:

a trailing edge; and

a divergent trailing edge device slideable along an aft surface of the trailing edge between a stowed position and a fully deployed position, the trailing edge device located entirely within the trailing edge when stowed, the trailing edge device increasing lift over drag of the wing when deployed.

2. The wing of claim 1, wherein the trailing edge device extends beneath a lower surface of the trailing edge when deployed.

3. The wing of claim 1, wherein chord length of the trailing edge device is between about 1% and 6% of chord length of the wing.

4. The wing of claim 1, wherein the divergent trailing edge device is mounted to a moveable flight control surface of the trailing edge.

5. The wing of claim 1, wherein the divergent trailing edge device is mounted to a fixed surface of the trailing edge.

6. The wing of claim 1, wherein the divergent trailing edge device has a divergence angle that varies as the device is being deployed.

7. The wing of claim 1, further comprising an actuator assembly contained entirely within the trailing edge for sliding the divergent trailing edge device.

8. The wing of claim 1, wherein the divergent trailing edge device includes a stiffened curved panel.

9. The wing of claim 1, wherein the trailing edge device includes a stiffened panel that is substantially straight.

10. The wing of claim 1, wherein an upper surface of the divergent trailing edge device includes ribs that make contact with an aft lower surface of the trailing edge.

11. The wing of claim 10, wherein the aft lower surface of the trailing edge also has ribs, which interlock with the ribs of the trailing edge device.

12. The wing of claim 1, further comprising a cover on a lower surface of the divergent trailing edge device, the cover providing a sliding surface for the divergent trailing edge device.

13. The wing of claim 1, wherein the trailing edge includes a cover on an upper surface of the divergent trailing edge device.

14. The wing of claim 1, further comprising at least one additional divergent trailing edge device slidable along the aft surface of the trailing edge, each additional divergent trailing edge device slideable between a stowed position and a deployed position.

15. The wing of claim 14, further comprising a plurality of actuators for independently control of each divergent trailing edge device.

16. An aircraft comprising:

a wing including a trailing edge having a moveable flight control surface and a fixed surface;

a plurality of divergent trailing edge devices integrated with the moveable flight control surface, each divergent trailing edge device slideable between a stowed position entirely within the moveable flight control surface and a deployed position at least partially under the moveable flight control surface; and

a plurality of actuators for independent control of the divergent trailing edge devices.

17. The aircraft of claim 16, wherein at least one additional divergent trailing edge device is integrated with the fixed surface, each additional divergent trailing edge device slideable between a stowed position entirely within the fixed surface and a deployed position at least partially under the fixed surface.

18. A method performed during flight of an aircraft, the method comprising sliding a divergent trailing edge device along a trailing edge of each aircraft wing to reduce lift over drag (L/D) of the wing;

and thereafter stowing the divergent trailing edge device entirely within the trailing edge.

19. The method of claim 18, further comprising selectively sliding and stowing at least one additional divergent trailing edge device along the trailing edge, wherein the divergent trailing edge devices are selectively deployed and stowed to vary L/D of the wing.

20. The method of claim 18, wherein the divergent trailing edge device is stowed entirely within a moveable flight control surface of the trailing edge.