초록 ▼

An actuation apparatus for a control flap which is disposed on the trailing edge of the wing of an aircraft and which can be displaced between a stowed position and an extended position, in which it is displaced rearwardly relative to the trailing edge of the wing and angled downwardly relative to t

An actuation apparatus for a control flap which is disposed on the trailing edge of the wing of an aircraft and which can be displaced between a stowed position and an extended position, in which it is displaced rearwardly relative to the trailing edge of the wing and angled downwardly relative to the wing plane; and corresponding intermediate positions. The actuation apparatus has a pyramid mechanism arrangement connected, on the one hand, to the load-bearing structure of the wing and, on the other hand, to the control flap, with at least one virtual axis which lies, in particular, at a finite distance from the plane of the wing profile and relative to which the control flap can be displaced.

대표청구항 ▼

What is claimed is: 1. Actuation apparatus for moving two structural parts relative to each other between a stowed position and an extended position with a rotational and a translational component, wherein the actuation apparatus comprises at least one adjustment unit, which is connected at a first

What is claimed is: 1. Actuation apparatus for moving two structural parts relative to each other between a stowed position and an extended position with a rotational and a translational component, wherein the actuation apparatus comprises at least one adjustment unit, which is connected at a first end to the load-bearing structure of a wing and at a second end to a control flap, with at least one virtual axis of rotation lying at a finite distance from a plane of the wing, and driving means, with respect to which the structural parts can be displaced in relation to each other, further wherein the actuation apparatus comprises a pyramid mechanism arrangement which changes the distance of the control flap from a trailing edge of the wing, and an adjustment device, which is mechanically coupled to the pyramid mechanism arrangement and adjusts the angle of the control flap. 2. Actuation apparatus as claimed in claim 1, wherein the adjustment device is formed by a second pyramid mechanism, which is mechanically connected in series with a first pyramid mechanism of the pyramid mechanism arrangement between the load-bearing structure of the wing and the control flap. 3. Actuation apparatus as claimed in claim 1, wherein the pyramid mechanism arrangement comprises first and second pyramid mechanisms, which are mechanically connected in series between the load-bearing structure of the wing and the control flap. 4. Actuation apparatus as claimed in claim 2, wherein the first and second pyramid mechanisms have virtual axes of rotation, which are located at different distances. 5. Actuation apparatus as claimed in claim 4, wherein the first pyramid mechanism, which is disposed closer to the wing, has a more remote virtual axis of rotation than the virtual axis of rotation of the second pyramid mechanism, which is disposed closer to the control flap. 6. Actuation apparatus as claimed in claim 5, wherein the more remote virtual axis of rotation is at infinity, such that movement of the control flap attributable to the first pyramid mechanism is a translating motion. 7. Actuation apparatus as claimed in claim 5, wherein the first and second pyramid mechanisms each have a first leg and a second leg, each said pair of first and second legs at one end being flexibly interconnected by a common pivot axis and at their respectively opposite ends being connected directly or indirectly to the wing via a first end axis and directly or indirectly to the control flap via a second end axis. 8. Actuation apparatus as claimed in claim 7, wherein the first and the second end axis and the pivot axis intersect at a common vertex, which lies on the virtual axis of rotation. 9. Actuation apparatus as claimed in claim 7, wherein the first leg of the first pyramid mechanism with its first end axis is connected to the load-bearing structure of the wing at a point which, as seen in the direction parallel to the virtual axis of rotation, is laterally offset by a distance that substantially corresponds to the length of the first leg relative to the point at which the second leg with its one end axis is connected directly or indirectly to the control flap. 10. Actuation apparatus as claimed in claim 7, wherein the first leg of the first pyramid mechanism with its first end axis is connected to the load-bearing structure of the wing at a point which, as seen in the direction of the profile depth, lies essentially in front of the point at which the second leg with its second end axis is connected directly or indirectly to the control flap. 11. Actuation apparatus as claimed in any one of claim 7, wherein the second pyramid mechanisms are mechanically connected in series behind the first pyramid mechanisms, wherein the first leg of the second pyramid mechanisms with its first end axis is connected to or shares the second end axis of the first pyramid mechanisms and wherein the second leg of the second pyramid mechanisms with its second end axis is connected to the control flap at a point which, as seen in the direction of the profile depth, lies essentially behind the point at which the first leg with its first end axis is connected to the first pyramid mechanism. 12. Actuation apparatus as claimed in claim 1, wherein the actuation apparatus comprises a single pyramid mechanism arrangement, which serves both to change the distance of the control flap from the trailing edge of the wing and to adjust the angle of the control flap. 13. Actuation apparatus as claimed in claim 1, wherein the driving means for retracting and extending the control flap comprises a rotary actuator device coupled to the first pyramid mechanism. 14. Actuation apparatus as claimed in claim 13, wherein the rotary actuator device is coupled to and driven by a drive shaft extending substantially in the direction of the length of the wing. 15. Actuation apparatus as claimed in claim 1, wherein the second pyramid mechanisms are coupled to and driven by the first pyramid mechanisms. 16. Actuation apparatus as claimed in claim 15, wherein the first legs of the second pyramid mechanisms are coupled to or integral with and driven by the second legs of the first pyramid mechanisms. 17. Actuation apparatus as claimed in claim 1, wherein one of the structural parts is a wing and the other of the structural parts is a control flap of an aircraft.