| 摘要 |
The invention relates to a vortex generator arrangement for an aircraft, comprising a surface section (2), which is intended to have a flow flowing over it and in which an opening (3) is provided, a flap element (4) which is pivotable between a first position, in which it extends in the plane of the surface section (2), and a second position, in which it extends out of the plane of the surface section (2), a biasing arrangement (15) by means of which the flap element (4) is biased towards the second position, a first retaining device (13) for retaining the flap element (4) in the first position, a second retaining device (21) for retaining the flap element (4) in the second position against a torque acting on the flap element (4) towards the first position, and a release device (17) for releasing the flap element (4) from the first retaining device (13). The biasing arrangement (15), the first retaining device (13) and the second retaining device (21) are configured in such a manner that the second retaining device (21) automatically retains the flap element (4) in the second position after the flap element (4) has been pivoted by the biasing arrangement (15) from the first position into the second position. As soon as the torque exceeds a predetermined value, the second retaining device (21) automatically releases the flap element (4), and the flap element (4) pivots against the force of the biasing arrangement (15) into the first position and is automatically retained therein by the first retaining device (13). |
