| 摘要 |
The invention relates to a flight control device for an aircraft, comprising a link lever, mechanical means for limiting an angular course of the link lever, first means (4) for generating a force for the return of the link lever about said rotational axis, and second means (16) for generating a force for the return of the link lever, which are arranged in parallel to the first means, at least one element of the second means and the link lever comprising mechanical means for the temporary connection thereof, which are arranged so as to be active when the link lever is moved beyond a pre-determined angular position in the angular range so that the second means are connected to the link lever. |
