Slat-Cove Filler for Wing Structure of an Aircraft

Patent metadata

Field	Value
Publication number	US-2021237850-A1
Application number	US-202117222604-A
Country	US
Kind code	A1
Filing date	Apr 5, 2021
Priority date	Oct 12, 2017
Publication date	Aug 5, 2021
Grant date	—

Abstract

Methods, systems and devices of the various embodiments may provide slat-cove fillers configured to reduce leading-edge slat noise on aircraft, such as transport aircraft.

First claim

What is claimed is:

1 . A wing structure for an aircraft, comprising:
a primary wing structure; a leading-edge slat comprising:
a cove wall;
a sliding-flexure-hinge extending from the cove wall; and
an interior space within the leading-edge slat, wherein the leading-edge slat is configured to movably interconnect with the primary wing structure for movement between a retracted position and a deployed position;
a slat-cove filler comprising a flexible material and defining a first shape when the leading-edge slat is in the deployed position and a second shape when the leading-edge slat is in the retracted position, wherein a leading end of the slat-cove filler is configured to slide along the sliding-flexure-hinge into the interior space when the leading-edge slat is moving toward the deployed position and out of the interior space when the leading-edge slat is moving toward the retracted position; and wherein the slat-cove filler comprises an internal auxiliary slat-cove filler component having a first component end and a second component end, the internal auxiliary slat-cove filler component attached at the first end to a trailing portion of the slat-cove filler facing the cove wall and the second end to the cove wall forward of the attachment to the slat-cove filler, the internal auxiliary slat-cove filler component configured to be disposed in a curved manner in the interior space between the cove wall and slat-cove filler when the leading-edge slat is in the deployed position, with at least one concavity of the internal auxiliary slat-cove filler component open to the cove wall.

2 . The wing structure of claim 1 , wherein the leading end of the slat-cove filler includes a mechanical stop.

3 . The wing structure of claim 2 , wherein the sliding-flexure-hinge is a bulbous type sliding-flexure-hinge.

4 . The wing structure of claim 2 , wherein the sliding-flexure-hinge includes at least one roller in rolling engagement with the slat-cove filler.

5 . The wing structure of claim 2 , wherein the leading end of the slat-cove filler includes a bias element configured to apply a bias force to the mechanical stop or directly to the leading end of the slat-cove filler itself.

6 . The wing structure of claim 1 , wherein at least a portion of the slat-cove filler comprises shape memory (SM) effect shape memory alloy (SMA) material.

7 . The wing structure of claim 6 , wherein the shape memory (SM) effect shape memory alloy (SMA) material is selected to have a predetermined application temperature below a finish temperature for transformation to martensite.

8 . The wing structure of claim 6 , wherein the at least a portion of the slat-cove filler comprising shape memory (SM) effect shape memory alloy (SMA) material is configured such that the application of heat to the at least a portion of the slat-cove filler causes the leading end of the slat-cove filler to slide along the sliding-flexure-hinge into the interior space when the leading-edge slat is moving toward the deployed position.

9 . The wing structure of claim 8 , wherein the application of heat to the at least a portion of the slat-cove filler further causes the slat-cover filler to achieve a desired shape relative to the wing structure.

10 . The wing structure of claim 8 , wherein the at least a portion of the slat-cove filler comprising shape memory (SM) effect shape memory alloy (SMA) material includes the internal auxiliary slat-cove filler component.

11 . A wing structure for an aircraft, comprising:
a primary wing structure; a leading-edge slat comprising:
a cove wall;
a sliding-flexure-hinge extending from the cove wall; and
an interior space within the leading-edge slat, wherein the leading-edge slat is configured to movably interconnect with the primary wing structure for movement between a retracted position and a deployed position; and

a slat-cove filler comprising a flexible material and defining a first shape when the leading-edge slat is in the deployed position and a second shape when the leading-edge slat is in the retracted position, wherein a leading end of the slat-cove filler is configured to slide along the sliding-flexure-hinge into the interior space when the leading-edge slat is moving toward the deployed position and out of the interior space when the leading-edge slat is moving toward the retracted position; wherein at least a portion of the slat-cove filler comprises shape memory (SM) effect shape memory alloy (SMA) material, wherein the shape memory (SM) effect shape memory alloy (SMA) material is selected to have a predetermined application temperature below a finish temperature for transformation to martensite.

12 . The wing structure of claim 11 , wherein the at least a portion of the slat-cove filler comprising shape memory (SM) effect shape memory alloy (SMA) material is configured such that application of heat to the at least a portion of the slat-cove filler causes the leading end of the slat-cove filler to slide along the sliding-flexure-hinge into the interior space when the leading-edge slat is moving toward the deployed position.

13 . The wing structure of claim 12 , wherein the application of heat to the at least a portion of the slat-cove filler further causes the slat-cover filler to achieve a desired shape relative to the wing structure.

14 . The wing structure of claim 11 , wherein the leading end of the slat-cove filler includes a mechanical stop.

15 . The wing structure of claim 14 , wherein the sliding-flexure-hinge is a bulbous type sliding-flexure-hinge.

16 . The wing structure of claim 14 , wherein the sliding-flexure-hinge includes at least one roller in rolling engagement with the slat-cove filler.

17 . The wing structure of claim 14 , wherein the leading end of the slat-cove filler includes a bias element configured to apply a bias force to the mechanical stop or directly to the leading end of the slat-cove filler itself.

18 . The wing structure of claim 11 , wherein the leading end of the slat-cove filler further comprises an internal auxiliary slat-cove filler component having a first component end and a second component end, the internal auxiliary slat-cove filler component attached at the first end to a trailing portion of the slat-cove filler facing the cove wall and the second end to the cove wall forward of the attachment to the slat-cove filler, the internal auxiliary slat-cove filler component configured to be disposed in a curved manner in the interior space between the cove wall and slat-cove filler when the leading-edge slat is in the deployed position, with at least one concavity of the internal auxiliary slat-cove filler component open to the cove wall.

19 . The wing structure of claim 18 , wherein the at least a portion of the slat-cove filler comprising shape memory (SM) effect shape memory alloy (SMA) material includes the internal auxiliary slat-cove filler component.

Assignees

• Nasa

Inventors

• Turner Travis L
• Brynildsen Scott E
• Mulvaney John W
• Allen Albert R
• Lockard David P
• Streett Craig L
• Khorrami Mehdi R

Classifications

• B64C9/22

  at the front of the wing · CPC title

• Y02T50/30

  Wing lift efficiency · CPC title

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C9/08

  bodily displaceable · CPC title

• B64C9/24 Primary

  by single flap · CPC title