Wing assembly with a main wing and movable high-lift body and a method for adjusting a high-lift body relative to a main wing

Patent metadata

Field	Value
Publication number	US-9334043-B2
Application number	US-201314138715-A
Country	US
Kind code	B2
Filing date	Dec 23, 2013
Priority date	Jun 28, 2011
Publication date	May 10, 2016
Grant date	May 10, 2016

Abstract

A wing assembly and method for operating the wing assembly, the assembly having a main wing and high-lift body movably coupled to the leading edge of the main wing, the coupling achieved by a driving device, an adjusting lever arrangement having a first main wing lever coupled to the main wing formed between a first adjusting lever pivot joint and the high-lift body as well as a second main wing lever coupled to the main wing so as to form an effective lever arm between a second adjusting lever pivot joint and a first adjusting lever pivot joint, and at least one adjusting lever non-rotatably coupled to the high-lift body, the high-lift body being movable between an initial position and a maximally adjusted position with respect to the initial position, at least one guide mechanism aiding movement of the high-lift body.

First claim

The invention claimed is:

1. A wing assembly comprising a main wing, at least one high-lift body on the leading edge of the main wing such that the high-lift body can be moved between an initial adjusting position and a maximally changed adjusting position with respect to the initial adjusting position, at least one guide mechanism by which the high-lift body is movably coupled to the main wing, and a driving device for adjusting the high-lift body, wherein the at least one guide mechanism comprises:
an adjusting lever arrangement comprising at least one adjusting lever, wherein at least one of the at least one adjusting levers of the adjusting lever arrangement is non-rotatably coupled to the high-lift body,
at least one first main wing lever that is coupled to the main wing by a first main wing pivot joint and to at least one of the at least one adjusting levers by a first adjusting lever pivot joint such that an effective lever arm is formed between the first adjusting lever pivot joint and the high-lift body,
at least one second main wing lever that is coupled to the main wing by a second main wing pivot joint and to at least one of the at least one adjusting levers by a second adjusting lever pivot joint such that an effective lever arm is formed between the second adjusting lever pivot joint and the first adjusting lever pivot joint,
wherein the at least one guide mechanism is realized in such a way that the first main wing pivot joint is arranged underneath the first adjusting lever pivot joint and the second main wing pivot joint is arranged above the second adjusting lever pivot joint with respect to a main wing thickness direction in the initial adjusting position of the high-lift body;
or
wherein the at least one guide mechanism is realized in such a way that the first main wing pivot joint is arranged above the first adjusting lever pivot joint and the second main wing pivot joint is arranged underneath the second adjusting lever pivot joint with respect to a main wing thickness direction in the initial adjusting position of the high-lift body.

2. The wing assembly of claim 1 , wherein the at least one guide mechanism is designed in such a way that the high-lift body comprises a trailing edge such that a contour line of the high-lift body extending along the wingspan direction thereof and the trailing edge of the high-lift body extend, at least sectionally, at one or more of a predetermined constant distance or a relatively small, aerodynamically ineffective distance from the contour surface of the main wing while the high-lift body is adjusted,
wherein the high-lift body is guided by the at least one guide mechanism in such a way during the movement of the high-lift body that, between the high-lift body's initial adjusting position and maximally changed adjusting positions, a rearmost contour line of the high-lift body with respect to a high-lift body chord direction is spaced apart from an outer contour surface of the main wing by no more than 10 mm at least in a first and a second contour surface section of the main wing or in an entire adjusting range of the high-lift body.

3. The wing assembly of claim 1 , wherein
an outer contour surface of the main wing in a region of the trailing edge of the high-lift body comprises, in the high-lift body's initial adjusting position, a first contour surface section that, viewed in a main wing chord direction, is behind a rearmost contour line of the high-lift body with respect to a high-lift body chord direction and covered by the high-lift body, as well as a second contour surface section that is behind the first contour surface section, viewed in the main wing chord direction,
profile lines extending along the main wing chord direction in the first and the second contour surface section comprise no sharp bends,
wherein the lengths of the first contour surface section and the second contour surface section in the high-lift body chord direction respectively correspond to half of a maximum thickness of the high-lift body.

4. The wing assembly of claim 1 , wherein the first and the second adjusting lever pivot joints comprise spherical joints.

5. The wing assembly of claim 1 , wherein the main wing pivot joints of a first guide mechanism of the at least one guide mechanism and one or more of the first adjusting lever pivot joint and the second adjusting lever pivot joint comprise spherical joints and at least one main wing pivot joint of a second guide mechanism of the at least one guide mechanism comprises an axial joint with an axis of rotation that extends along a wingspan direction of the high-lift body.

6. The wing assembly of claim 1 , wherein
one or more of the first adjusting lever pivot joints of a first guide mechanism of the at least one guide mechanism and a second adjusting lever pivot joint of a second guide mechanism of the at least one guide mechanism comprise axial joints that respectively allow an axial movement, wherein an axial joint component is respectively fixed in a main wing wingspan direction by the at least one first and second main wing levers, and
at least one of each of the at least first and second main wing levers are respectively coupled to the other first or second adjusting lever pivot joint in such a way that the adjusting lever pivot joints are fixed in the main wing wingspan direction.

7. The wing assembly of claim 1 , wherein the adjusting lever arrangement of the at least one guide mechanism comprises at least two adjusting levers, wherein
the adjusting levers of the adjusting lever arrangement are respectively coupled to the high-lift body in a rotationally rigid fashion, at least with respect to rotations about a high-lift body wingspan direction, wherein at least a first adjusting lever of the at least two adjusting levers of the adjusting lever arrangement is coupled to the first main wing lever by the first adjusting lever pivot joint and at least a second adjusting lever of the at least two adjusting levers of the adjusting lever arrangement is coupled to the second main wing lever by the second adjusting lever pivot joint,
or
a first adjusting lever of the at least two adjusting levers of the adjusting lever arrangement is coupled to the main wing by at least one first main wing lever that is coupled thereto by at least one first main wing pivot joint and coupled to the at least one first adjusting lever by the first adjusting lever pivot joint, wherein the first adjusting lever is also coupled to the main wing by at least one second main wing lever that is coupled to the first adjusting lever by the second adjusting lever pivot joint and respectively coupled to the main wing by the at least one second main wing pivot joint, wherein at least one second adjusting lever of the at least two adjusting levers of the adjusting lever arrangement is coupled to the high-lift body in a rotationally rigid fashion, at least with respect to rotations about a high-lift body wingspan direction, and wherein the at least one second adjusting lever of the at least two adjusting levers of the adjusting lever arrangement is coupled to the first adjusting lever of the at least two adjusting levers of the adjusting lever arrangement in such a way that adjusting movements carried out thereby and one or more of translatory adjusting movements in a high-lift body chord direction and a high-lift body thickness direction and rotatory adjusting movements about a high-lift body wingspan direction are transmitted to the at least one second adjusting lever of the at least two adjusting levers of the adjusting lever arrangement.

8. The wing assembly of claim 1 , wherein the driving device comprises at least one actuator that is connected to the main wing to move at least one of the at leas

Assignees

• Airbus Operations Gmbh

Inventors

• Schlipf Bernhard
• Triebl Carsten

Classifications

• B64C9/24

  by single flap · CPC title

• Y02T50/145

  Cross-Sectional Technologies · mapped topic

• Y02T50/32

  Cross-Sectional Technologies · mapped topic

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C3/50

  by leading or trailing edge flaps · CPC title