Seal assemblies for use with drooped spoilers and other control surfaces on aircraft

• US 7,611,099 B2
• Filed: 09/07/2005
• Issued: 11/03/2009
• Est. Priority Date: 09/07/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kordel, Jan A., Glassmoyer, Christopher G., Bowers, Bret A., Williams, Darren B., Sakurai, Seiya
• Primary Examiner(s): Mansen; Michael R
• Assistant Examiner(s): Bonzell; Philip J
• Application Number:
  US11/220,446
• Publication Number:
  US 20070252040A1
• Time in Patent Office: 1,518 Days
• Field of Search: 244/132, 244/213, 244/215, 244/216
• US Class Current: 244/215
• CPC Class Codes: B64C 2009/143 comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps
• CPC Class Codes: B64C 7/00 Structures or fairings not otherwise provided for
• CPC Class Codes: B64C 9/18 by single flaps
• CPC Class Codes: Y02T 50/30 Wing lift efficiency
• CPC Class Codes: Y10S 277/916 Seal including vibration dampening feature

Abstract

Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.

Claims

1. A seal assembly for use with an aircraft, the aircraft having a movable control surface spaced apart from a fixed airfoil portion to define a gap therebetween, the seal assembly comprising:

a first seal member having a first proximal portion and a first distal portion, wherein the first proximal portion is fixedly attached to the fixed airfoil portion and the first distal portion extends outwardly from the fixed airfoil portion toward the movable control surface; and

a second seal member having a second proximal portion and a second distal portion, wherein the second proximal portion is fixedly attached to the movable control surface and the second distal portion extends outwardly from the movable control surface toward the fixed airfoil portion, and wherein the second distal portion movably contacts the first distal portion of the first seal member to cover the gap between the fixed airfoil portion and the movable control surface as the movable control surface moves relative to the fixed airfoil portion;

wherein the second distal portion of the second seal member presses against the first distal portion of the first seal member and deflects the first seal member changing a radius thereof as the movable control surface rotates in a first direction; and

wherein the second distal portion separates from the first distal portion when the movable control surface rotates in a second direction opposite to the first direction.

2. The seal assembly of claim 1 wherein the second distal portion of the second seal member is configured to press against the first distal portion of the first seal member and deflect the first seal member as the movable control surface moves relative to the fixed airfoil portion.

3. The seal assembly of claim 1 wherein the first distal portion of the first seal member is configured to press against the second distal portion of the second seal member and deflect the second seal member as the movable control surface moves relative to the fixed airfoil portion.

4. The seal assembly of claim 1 wherein the movable control surface includes a spoiler and the fixed airfoil portion includes a fixed wing portion, wherein the second distal portion of the second seal member is configured to press against the first distal portion of the first seal member as the spoiler rotates downwardly relative to the fixed wing portion, and wherein the second distal portion is configured to separate from the first distal portion when the spoiler rotates upwardly relative to the fixed wing portion.

5. The seal assembly of claim 1, further comprising a vibration damper configured to be operably coupled to the first distal portion of the first seal member.

6. The seal assembly of claim 1 wherein the movable control surface includes a spoiler and the fixed airfoil portion includes a fixed wing portion, wherein the first seal member includes a resilient metal outer layer and the second seal member includes a stiff plastic inner surface configured slide across the resilient metal outer layer, and wherein the seal assembly further comprises:

a damper support configured to be fixedly attached to the fixed wing portion; and

a vibration damper configured to be operably coupled to the first distal portion of the first seal member and carried by the damper support.

10. The seal assembly of claim 1 wherein the first distal portion includes a first surface and the second distal portion includes a second surface, and wherein the second surface is configured to slide across the first surface as the movable control surface moves relative to the fixed airfoil portion.

7. A seal assembly for use with an aircraft, the aircraft having a movable control surface spaced apart from a fixed airfoil portion to define a gap therebetween, the seal assembly comprising:

a first seal member having a first proximal portion and a first distal portion, wherein the first proximal portion is fixedly attached to the fixed airfoil portion and the first distal portion extends outwardly from the fixed airfoil portion toward the movable control surface; and

a second seal member having a second proximal portion and a second distal portion, wherein the second proximal portion is fixedly attached to the movable control surface and the second distal portion extends outwardly from the movable control surface toward the fixed airfoil portion, and wherein the second distal portion moveably contacts the first distal portion of the first seal member to at least partially cover the gap between the first airfoil portion and the movable control surface as the movable control surface rotates downwardly relative to the fixed airfoil portion;

wherein the gap is uncovered between the movable control surface and the fixed airfoil portion as the movable control surface rotates upwardly relative to the fixed airfoil portion;

wherein the first distal portion includes an outer-facing surface and the second distal portion includes an inner-facing surface, and wherein the inner-facing surface is configured to slide across the outer-facing surface as the movable control surface moves relative to the fixed airfoil portion.

8. The seal assembly of claim 7 wherein the first seal member is formed from a resilient material and the second seal member is formed from a stiff material that is different than the resilient material.

9. The seal assembly of claim 7 wherein the first seal member is formed from a resilient metal and the second seal member is formed from a stiff plastic.

11. A seal assembly for use with an aircraft, the aircraft having a movable control surface spaced apart from a fixed airfoil portion to define a gap therebetween, the seal assembly comprising:

a first seal member having a first proximal portion and a first distal portion, wherein the first proximal portion is fixedly attached to the fixed airfoil portion and the first distal portion extends outwardly from the fixed airfoil portion toward the movable control surface;

a second seal member having a second proximal portion and a second distal portion, wherein the second proximal portion is fixedly attached to the movable control surface and the second distal portion extends outwardly from the movable control surface toward the fixed airfoil portion, and wherein the second distal portion movably contacts the first distal portion of the first seal member to cover the gap between the fixed airfoil portion and the movable control surface as the movable control surface moves relative to the fixed airfoil portion;

a damper support fixedly attached to the fixed airfoil portion; and

a vibration damper directly attached to the first distal portion of the first seal member and carried by the damper support.

12. A Method for sealing a gap between a movable control surface and a fixed airfoil portion on an aircraft, the method comprising:

fixedly attaching a first proximal portion of a first seal member to the fixed airfoil portion, whereby a first distal portion of the first seal member extends outwardly from the fixed airfoil portion toward the movable control surface;

pressing inwardly against the first distal portion of the first seal member with a second distal portion of a second seal member;

fixedly attaching a second proximal portion of the second seal member to the movable control surface;

fixedly attaching a damper support to the fixed airfoil portion; and

positioning a motion damper between the damper support and the first distal portion of the first seal member.

13. The method of claim 12 wherein pressing inwardly against the first distal portion of the first seal member includes pressing inwardly against a resilient metal layer to deflect the resilient metal layer.

14. The method of claim 12 wherein fixedly attaching a first proximal portion of a first seal member to the fixed airfoil portion includes fixedly attaching a piece of stainless steel to a trailing edge region of a wing.

15. The method of claim 12 wherein fixedly attaching a first proximal portion of a first seal member to the fixed airfoil portion includes fixedly attaching a resilient piece of stainless steel to a trailing edge region of a wing, and wherein fixedly attaching a second proximal portion of the second seal member to the movable control surface includes fixedly attaching a stiff piece of plastic to a leading edge region of a wing spoiler.

16. The method of claim 12 wherein fixedly attaching a first proximal portion of a first seal member to the fixed airfoil portion includes fixedly attaching a resilient piece of stainless steel to a trailing edge region of a wing, wherein fixedly attaching a second proximal portion of the second seal member to the movable control surface includes fixedly attaching a stiff piece of plastic to a leading edge region of a wing spoiler, and wherein pressing inwardly against the first distal portion of the first seal member with a second distal portion of a second seal member includes pressing inwardly against the stainless steel with the stiff piece of plastic.

17. An aircraft having a system for sealing a gap between a spoiler and a fixed wing portion, the system comprising:

first seal means fixedly attached to the fixed wing portion;

second seal means fixedly attached to the spoiler; and

means for pressing a first distal portion of the first seal means against a second distal portion of the second seal means to maintain contact between the first and second seal means and at least partially cover the gap as the spoiler rotates downwardly relative to the fixed wing portion, wherein the system further comprises means for uncovering the gap between the spoiler and the fixed wing portion as the spoiler rotates upwardly relative to the fixed wing portion, and

means for dampening vibrations of the first seal means.

18. A seal assembly for use with an aircraft, the aircraft having a movable control surface spaced apart from a fixed airfoil portion to define a gap therebetween, the seal assembly comprising:

a first seal member formed from resilient material, the first seal member having a first proximal portion and a first distal portion, wherein the first proximal portion is fixedly attached to the fixed airfoil portion, wherein the first distal portion extends outwardly from the fixed airfoil portion toward the movable control surface, and wherein the first distal portion includes an outer-facing surface;

a second seal member formed from stiff material that is different than the resilient material, the second seal member having a second proximal portion and a second distal portion, wherein the second proximal portion is fixedly attached to the movable control surface, wherein the second distal portion includes an inner-facing surface that presses against the outer-facing surface of the first distal portion and deflects the first seal member into a decreased radius as the movable control surface rotates downwardly relative to the fixed airfoil portion, and wherein the second distal portion separates from the first distal portion to form a gap therebetween when the movable control surface rotates upwardly relative to the fixed airfoil portion;

a damper support fixedly attached to the fixed airfoil portion; and

a vibration damper carried by the damper support and operably coupled to the first distal portion of the first seal member.