Flexible control surface for an aircraft

Details Flexible control surface for an aircraft Flexible control surface for an aircraft

B - Operations, Transporting

64

C

B64C 3/48 (2006.01) B64C 3/50 (2006.01) B64C 9/00 (2006.01)

Patent

CA 2634519

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.

L~invention concerne une surface de commande flexible (1 ; 11, 14) comprenant au moins deux actionneurs (3) sollicitant la surface de commande (1 ; 11, 14) en différents points de sollicitation (2) mutuellement décalés latéralement par rapport au sens (6) d~un écoulement circulant. Lesdits au moins deux actionneurs (3) sont conçus de telle sorte que les points de sollicitation (2) puissent être déformés indépendamment lors d~un fonctionnement simultané des actionneurs (3). Il est donc possible de déformer élastiquement la surface de commande (1 ; 11, 14), notamment dans le sens de la largeur d~envergure (9), sans créer de vrilles, et d~obtenir ainsi des transitions uniformes le long de la surface de commande latéralement par rapport au sens (6) de l~écoulement. L~invention permet de réduire les tourbillons et les parasites induits par la surface de commande.

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