FLEXIBLE CONTROL SURFACE FOR AN AIRCRAFT

摘要

A flexible control surface (1; 11, 14) comprises at least two actuators (3), which act on the control surface (1; 11, 14) at different points of action (2) which are offset laterally with respect to the circulating-flow direction (6) with respect to one another. The at least two actuators (3) are designed such that the points of action (2) can be deflected differently when the actuators (3) are operated at the same time. It is thus possible to elastically deform the control surface (1; 11, 14), in particular along the span width direction (9), without kinks, in which case it is possible to achieve uniform transitions along the control surface laterally with respect to the flow direction (6). The invention makes it possible to reduce vortices and noise induced by the control surface.