Vortex generator arrangement for an aircraft

Patent metadata

Field	Value
Publication number	US-10543908-B2
Application number	US-201615365133-A
Country	US
Kind code	B2
Filing date	Nov 30, 2016
Priority date	Dec 1, 2015
Publication date	Jan 28, 2020
Grant date	Jan 28, 2020

Abstract

A vortex generator arrangement for an aircraft, a flow control system and an aircraft comprising such vortex generator arrangement. The arrangement includes a surface portion facing a first region of space to constitute a flow surface, a vortex generating element, an element support structure connected to the element, a mounting structure. The element support structure and the element together are rotatable between first and second positions and a biasing device, retainer and release are provided. The rotational axis extends transversely with respect to the surface portion. The projection of the element onto a projection plane is smaller in the first rotational position than in the second rotational position, the projection plane extending perpendicularly to a tangent plane of the surface portion at a reference point of the surface portion and to a predetermined direction parallel to the extension of the tangent plane.

First claim

The invention claimed is:

1. A vortex generator arrangement for an aircraft, the vortex generator arrangement comprising:
a surface portion facing and bounding a first region of space, wherein the surface portion is configured to constitute a flow surface for a flow present in operation in the first region of space;
a vortex generating element disposed in the first region of space;
an element support structure rigidly connected to the vortex generating element;
a mounting structure to which the element support structure is mounted such that the element support structure and the vortex generating element together are rotatable, with respect to the mounting structure, about a rotational axis between a first rotational position and a second rotational position, wherein the rotational axis extends transversely with respect to the surface portion;
a biasing device configured to bias the vortex generating element towards the second rotational position;
a retainer configured to retain the vortex generating element in the first rotational position against a biasing provided by the biasing device; and
a release configured to release the vortex generating element from the retainer, such that it is moved into the second rotational position by the biasing device;
wherein the vortex generating element is disposed completely in the first region of space in each rotational position thereof about the rotational axis;
wherein a projection of the vortex generating element onto a projection plane is smaller in the first rotational position than in the second rotational position; and
wherein the projection plane extends perpendicularly to a tangent plane of the surface portion at a reference point of the surface portion and to a predetermined direction parallel to an extension of the tangent plane.

2. The vortex generator arrangement according to claim 1 , wherein the rotational axis extends perpendicularly with respect to the surface portion.

3. The vortex generator arrangement according to claim 1 , wherein the vortex generating element is a planar plate having a first extended surface, an opposite second extended surface, and a circumferential edge surface extending between the first and second extended surfaces.

4. The vortex generator arrangement according to claim 1 , wherein the vortex generating element extends from the surface portion or is spaced from the surface portion by an intermediate portion of the element support structure located inside the first region of space.

5. The vortex generator arrangement according to claim 1 , wherein at least a part of the surface portion is a surface of a flexible seal connected to both the mounting structure and the element support structure.

6. The vortex generator arrangement according to claim 1 , wherein the element support structure comprises a plate-shaped portion having a surface section constituting at least a part of the surface portion.

7. The vortex generator arrangement according to claim 1 , wherein:
the mounting structure comprises a housing defining an interior space, which constitutes a second region of space,
the biasing device, the retainer, the release, and at least a part of the element support structure are located inside the interior space of the housing, and
the surface portion is provided by an outer surface of the housing.

8. The vortex generator arrangement according to claim 1 , wherein the element support structure comprises an elongate shaft portion, which extends along and defines the rotational axis, and at least one projection, which extends radially from the shaft portion, and wherein the biasing device is configured to engage the at least one projection.

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

10. The vortex generator arrangement according to claim 1 , wherein the retainer comprises a lock that is movable between a locking position and a release position and is configured to engage a corresponding locking feature on the element support structure when the element support structure is in the first rotational position and the lock is in the locking position, such that movement of the element support structure from the first rotational position towards the second rotational position is prevented, and the release comprises an actuator configured to move the lock between the locking position and the release position.

11. The vortex generator arrangement according to claim 1 , wherein the retainer comprises a strap or a wire connecting the element support structure to the mounting structure to retain the element support structure in the first rotational position, and the release comprises a pyrotechnic cutter for cutting the strap or the wire to release the vortex generator from the retainer.

12. A flow control system comprising:
an aerodynamic body for an aircraft;
a plurality of vortex generator arrangements according to claim 1 arranged on the aerodynamic body such that the surface portion of each of the vortex generator arrangements forms a respective part of a surface of the aerodynamic body; and
a control unit configured to selectively actuate the release of one or more of the plurality of vortex generator arrangements.

13. The flow control system according to claim 12 , wherein:
the aerodynamic body comprises a base portion and a control portion movably coupled to the base portion such that the control portion is deflectable with respect to the base portion about a pivot axis from a first angular position towards a second angular position in one or both rotational directions;
the plurality of vortex generator arrangements are arranged along the pivot axis on the base portion or the control portion; and
the control unit is configured to actuate the release to release the element support structure from the retainer when a deflection of the control portion from the first angular position towards the second angular position exceeds a predetermined value.

14. An aircraft comprising a flow control system according to claim 12 , wherein each of the vortex generator arrangements is arranged such that, in flight of the aircraft, a flow over the surface portion of a respective one of the plurality of vortex generator arrangements is established.

15. The aircraft according to claim 14 , wherein the surface portion is a part of a surface of a wing, a vertical or horizontal tail plane, a flap, a slat, a rudder, or a high lift device of the aircraft.

16. An aircraft comprising one or more vortex generator arrangement according to claim 1 , each of the one or more vortex generator arrangements being arranged such that, in flight of the aircraft, a flow over the surface portion of a respective one of the one or more vortex generator arrangement is established.

17. The aircraft according to claim 16 , wherein the surface portion is a part of a surface of a wing, a vertical or horizontal tail plane, a flap, a slat, a rudder, or a high lift device of the aircraft.

18. The aircraft according to claim 16 , wherein the rotational axis extends perpendicularly with respect to the surface portion.

19. The aircraft according to claim 16 , wherein the vortex generating element is a planar plate having a first extended surface, an opposite second extended surface, and a circumferential edge surface extending between the first and second extended surfaces.

20. The aircraft according to claim 16 , wherein the vortex generating element extends from the surface portion or is spaced from the surface

Assignees

• Airbus Operations Gmbh

Inventors

• Stefes Bruno
• Eilken Wolfgang
• Paul Erich

Classifications

• B64C13/16

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

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C3/00

  Wings (ornithopter wings B64C33/02) · CPC title

• B64C9/14

  forming slots · CPC title

• B64C5/02

  Tailplanes · CPC title