Control surface of aircraft

Details Control surface of aircraft Control surface of aircraft

B - Operations, Transporting

64

C

B64C 9/02 (2006.01) B64C 9/04 (2006.01)

Patent

CA 2731787

Aircraft control surface (1), in particular for an aircraft lifting surface (2), that comprises a primary control surface (6) that comprises a hinge axis (10), and a secondary control surface (7) that comprises a hinge axis (11), with the secondary control surface (7) rotating by means of its hinge axis (11) relative to the primary control surface (6), said secondary control surface (7) only partially occupying the span of the primary control surface (6), the length of the secondary control surface (7) along its hinge axis (11) being significantly less than the length of the primary control surface (6) along its hinge axis (10), and moreover the width or chord of said secondary control surface (7) along the direction of its hinge axis (11) narrows significantly towards the tip of the lifting surface (2) according to a law of narrowing designed expressly for adapting the distribution of torsional stiffness along the span of the lifting surface (2) to the distribution of aerodynamic load thereon, whereas the distribution of effective curvature due to the deflection of said control surface (1) is such that it increases the stalling angle of the lifting surface (2).

L'invention concerne une surface de commande (1) d'aéronef, en particulier pour une surface porteuse (2) d'aéronef, comprenant une surface de commande primaire (6) qui comprend un axe de charnière (10), et une surface de commande secondaire (7) qui comprend un axe de charnière (11), la surface de commande secondaire (7) tournant sur son axe de charnière (11) par rapport à la surface de commande primaire (6), ladite surface de commande secondaire (7) occupant seulement en partie l'envergure de la surface de commande primaire (6), la longueur de la surface de commande secondaire (7) étant, le long de son axe de charnière (11), significativement inférieure à la longueur de la surface de commande primaire (6) le long de son axe de charnière (10), la largeur ou corde de ladite surface de commande secondaire (7) rétrécissant en outre significativement le long de la direction de son axe de charnière (11) vers la pointe de la surface porteuse (2) selon une loi de rétrécissement conçue expressément pour adapter la répartition de rigidité à la torsion le long de l'envergure de la surface porteuse (2) à la répartition de charge aérodynamique sur ladite surface, la distribution de courbure effective due à la déflexion de ladite surface de commande (1) étant également telle qu'elle augmente l'angle d'entrée en perte aérodynamique de la surface porteuse (2).

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