Vortex generator arrangement

Patent metadata

Field	Value
Publication number	US-10202187-B2
Application number	US-201615015804-A
Country	US
Kind code	B2
Filing date	Feb 4, 2016
Priority date	Feb 6, 2015
Publication date	Feb 12, 2019
Grant date	Feb 12, 2019

Abstract

A vortex generator arrangement for an aircraft including a surface section, a flap element pivotable between a first position and a second position, a biasing arrangement biasing the flap element towards the second position, retaining devices retaining the flap element in the first or second position, and a release device releasing the flap element from the first retaining device. The biasing arrangement, the first retaining device and the second retaining device are configured such that the second retaining device automatically retains the flap element in the second position after the flap element has been pivoted by the biasing arrangement from the first position into the second position. As soon as the torque exceeds a predetermined value, the second retaining device automatically releases the flap element, which pivots against the force of the biasing arrangement into the first position and is automatically retained therein by the first retaining device.

First claim

The invention claimed is:

1. A vortex generator arrangement for an aircraft, comprising:
a surface section, which is intended to have a flow flowing over it and in which an opening is provided;
a flap element which is supported pivotably about a pivot axis such that the flap element is pivotable between a first position, in which it extends in the plane of the surface section, and a second position, in which it extends out of the plane of the surface section;
a biasing arrangement by which the flap element is biased towards the second position;
a first retaining device, which is adapted to retain the flap element in the first position against the force of the biasing arrangement;
a second retaining device, which is adapted to retain the flap element in the second position against a torque acting on the flap element towards the first position; and
a release device, which is adapted to release the flap element from the first retaining device;
wherein the biasing arrangement, the first retaining device and the second retaining device are configured such that:
the second retaining device automatically retains the flap element in the second position after the flap element has been pivoted by the biasing arrangement from the first position into the second position; and
as soon as the torque exceeds a predetermined value, the second retaining device automatically releases the flap element and the flap element pivots against the force of the biasing arrangement into the first position and is automatically retained therein by the first retaining device.

2. The vortex generator arrangement according to claim 1 , wherein the first retaining device and/or the second retaining device is adapted to magnetically retain the flap element in the first position and in the second position, respectively.

3. The vortex generator arrangement according to claim 2 , wherein the first retaining device and/or the second retaining device comprises a permanent magnet arrangement, which is adapted to retain the flap element in the first position and in the second position, respectively.

4. The vortex generator arrangement according to claim 1 , wherein the flap element is part of a component, which is mounted pivotably about the pivot axis in such a manner that it comprises, with respect to the pivot axis, a first lever arm constituted by the flap element and a second lever arm, wherein the first retaining device and the second retaining device engage the second lever arm in order to retain the flap element in the first position and the second position, respectively, and wherein the biasing arrangement engages the second lever arm.

5. The vortex generator arrangement according to claim 1 , wherein the biasing arrangement comprises a spring element.

6. The vortex generator arrangement according to claim 1 , wherein the release device is adapted to release the flap element from the first retaining device automatically when a predetermined pressure is exceeded.

7. The vortex generator arrangement according to claim 6 , wherein the release device comprises a release element and the release device is configured in such a manner that when the flap element is in the first position the release element is spaced from the flap element below the predetermined pressure, and that upon exceeding the predetermined pressure the release element is moved such that it engages the flap element, if the flap element is in the first position, and exerts on the flap element a torque acting towards the second position, wherein the first retaining device is adapted to release the flap element from the first position when the release element exerts the force.

8. The vortex generator arrangement according to claim 7 , wherein the release device comprises a pressurized container having an opening which is closed by a membrane in a pressure-tight manner, wherein the membrane is connected to the release element and is configured such that it deforms when the predetermined pressure is exceeded and thereby effects the movement of the release element.

9. The vortex generator arrangement according to claim 1 , wherein in the second position the flap element projects from the surface section on one side thereof, and the biasing arrangement, the first retaining device, the second retaining device and/or the release device are disposed on the opposite side of the surface section.

10. The vortex generator arrangement according to claim 1 , comprising a housing having an interior space, which is accessible through the opening of the surface section and in which the biasing arrangement, the first retaining device, the second retaining device and/or the release device are disposed.

11. An aircraft having a vortex generator arrangement according to claim 1 , wherein the vortex generator arrangement is arranged such that in flight of the aircraft a flow over the surface section is generated, which flow acts on the flap element and exerts on the flap element a torque acting towards the first position when the flap element is in the second position.

12. The aircraft according to claim 11 , wherein the predetermined value of the torque is not exceeded in a take-off phase and in a landing phase of the aircraft and is reached prior to reaching a cruise speed of the aircraft.

13. The aircraft according to claim 11 , wherein the surface section is part of a surface of a wing, of a vertical stabilizer, of a horizontal tailplane, of a rudder, of a control flap, or of a high lift device.

Assignees

• Airbus Operations Gmbh

Inventors

• Hegenbart Matthias
• Eilken Wolfgang
• Paul Erich
• Stefes Bruno
• Duken Lena

Classifications

• Y02T50/162

  Cross-Sectional Technologies · mapped topic

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C23/06 Primary

  by generating vortices · CPC title

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title