Assembly for warping of an aerodynamic structure

Patent metadata

Field	Value
Publication number	US-11208194-B2
Application number	US-201916587804-A
Country	US
Kind code	B2
Filing date	Sep 30, 2019
Priority date	Oct 4, 2018
Publication date	Dec 28, 2021
Grant date	Dec 28, 2021

Abstract

A spar assembly for an aircraft wing extends between an upper cover and a lower cover and includes linkages spaced consecutively along the length of the spar assembly, each linkage extending from an upper pivot, to a lower pivot, thereby joining upper and lower attachment structures of the spar assembly together. Each linkage includes a pair of fixed-length links pivotably connected at one end about a center pivot and pivotably connected at respective other ends. The spar assembly includes a drive bar connected to the center pivot of each of the linkages, and an actuator arranged to move the drive bar along the length of the spar assembly. When the actuator moves the drive bar along the length of the spar structure, the links in each pair of links are rotated relative to each other about the center pivot, thereby moving the upper and lower covers and warping the wing.

First claim

The invention claimed is:

1. An aircraft wing comprising:
an upper cover;
lower cover;
a spar assembly extending between the upper cover and the lower cover, wherein the spar assembly comprises:
an upper attachment structure connected to the upper cover,
a lower attachment structure connected to the lower cover;
a multiplicity of linkages spaced along a length of the spar assembly, each of the linkages comprising a first link, which has a first end that is pivotably connected to and extends from an upper pivot on the upper attachment structure, and a second link, which has a first end that is pivotably connected to and extends from a lower pivot on the lower attachment structure, wherein the first link and the second link are pivotably connected, at respective second ends thereof, at a third pivot, thereby joining the upper and lower attachment structures together, and
a drive bar connected to the third pivot of each of the multiplicity of linkages;
wherein each linkage is adjustable, by adjusting a position of the third pivot, such that the first and second links are pivoted about the third pivot and a distance between the upper and lower pivots is altered, thereby enabling the wing to be warped, and
wherein, by adjusting the position of the third pivot, relative positions of the first and second links about the third pivot are respectively adjustable over a range of positions, wherein the range of positions includes a position in which the first, second, and third pivots are positioned in a straight line; and

an actuator arranged to move the drive bar, such that the actuator can simultaneously adjust the position of the multiplicity of third pivots.

2. The wing according to claim 1 , wherein the upper pivot and the lower pivot to which a same linkage of the multiplicity of linkages is connected are spaced apart from each other in a span direction of the wing.

3. The wing according to claim 1 , wherein each pair of first and second links is associated with a third link, the third link extending from the lower pivot to a fourth pivot, the fourth pivot being on the upper attachment structure.

4. The wing according to claim 3 , wherein the fourth pivot is coincident with an upper pivot of an adjacent linkage.

5. The wing according to claim 1 , wherein the spar assembly is a first spar assembly located along a relatively forward or rearward part of the upper and lower covers, the wing comprising a second spar assembly, located along another of the forward or rearward part of the covers.

6. A spar assembly for use as the spar assembly according to claim 1 .

7. An aircraft comprising the aircraft wing according to claim 1 .

8. A method of warping a wing on an aircraft, the method comprising:
connecting a spar assembly between upper and lower covers of the wing;
connecting an upper attachment structure of the spar assembly to the upper cover of the wing, wherein the upper attachment structure comprises a plurality of upper pivots;
connecting a lower attachment structure of the spar assembly to the lower cover of the wing, wherein the lower attachment structure comprises a plurality of lower pivots;
providing a multiplicity of linkages spaced apart in a span direction of the wing;
connecting, in a pivotable manner, a first end of a first link of each linkage to extend from one of the upper pivots on the upper attachment structure;
connecting, in a pivotable manner, a first end of a second link of each linkage to extend from one of the lower pivot points on the lower attachment structure;
connecting, in a pivotable manner and for each linkage, a second end of the first link to a second end of the second link at a third pivot to join the upper and lower attachment structures together;
connecting a drive bar to the third pivot of each of the multiplicity of linkages;
moving, using an actuator, the drive bar along the length of the spar assembly to simultaneously adjust the position of the multiplicity of third pivots;
actuating, by adjusting a position of the third pivot so that the first and second links are pivoted about the third pivot, the multiplicity of linkages from a first configuration, in which the upper and lower pivots are at a first spacing from each other, to a second configuration, in which the upper and lower pivots are at a second spacing from each other, wherein the first spacing is different from the second spacing, such that the wing is warped as the linkages are actuated between the first and second configurations;
wherein, by adjusting the position of the third pivot, relative positions of the first and second links about the third pivot are respectively adjustable over a range of positions, wherein the range of positions includes a position in which the first, second, and third pivots are positioned in a straight line.

9. The method according to claim 8 , wherein the upper pivot and the lower pivot to which a same linkage of the multiplicity of linkages is connected are spaced apart from each other in the span direction of the wing.

10. A spar assembly for extending between an upper cover and a lower cover on an aircraft wing, the spar assembly comprising:
an upper attachment structure for connecting to the upper cover;
a lower attachment structure for connecting to the lower cover;
a multiplicity of linkages spaced consecutively along a length of the spar assembly, each of the linkages comprising a first link, which has a first end that is pivotably connected to and extends from an upper pivot on the upper attachment structure, and a second link, which has a first end that is pivotably connected to and extends from a lower pivot on the lower attachment structure, wherein the first link and the second link are pivotably connected, at respective second ends thereof, at a third pivot, thereby joining the upper and lower attachment structures together;
a drive bar connected to the third pivot of each of the multiplicity of linkages; and
an actuator arranged to move the drive bar along the length of the spar assembly, such that the actuator can simultaneously adjust the position of the multiplicity of third pivots;
wherein each linkage is adjustable, by adjusting a position of the third pivot, such that the first and second links are pivoted about the third pivot and a distance between the upper and lower pivots is altered, thereby enabling the wing to be warped;
wherein, by adjusting the position of the third pivot, positions of the first and second links about the third pivot are respectively adjustable over a range of positions, wherein the range of positions includes a position in which the first, second, and third pivots are positioned in a straight line.

11. An aerodynamic structure comprising:
a first cover;
a second cover;
a shear-resisting assembly extending between the first cover and the second cover, wherein the shear-resisting assembly comprises:
a first attachment structure connected to the first cover;
a second attachment structure connected to the second cover; and
a multiplicity of linkages spaced along a length of the shear-resisting assembly, each of the linkages comprising a first link, which has a first end that is pivotably connected to and extends from a first pivot on the first attachment structure, and a second link, which has a first end that is pivotably connected to and extends from a second pivot on the second attachment structure, wherein the first link and the second link are pivotably connected, at respective second ends thereof, at a third pivot, thereby joining the first and second attachment structures together,
wherein each linkage is adjustable, by adjusting a position of the third pivot, such that the first and sec

Assignees

• Airbus Operations Ltd

Inventors

• Brakes David
• Custance Denys

Classifications

• B64C13/30

  using cable, chain, or rod mechanisms · CPC title

• B64C3/185

  Spars · CPC title

• B64C3/52 Primary

  Warping · CPC title