Aircraft

Details Aircraft Aircraft

B - Operations, Transporting

64

C

B64C 9/16 (2006.01) B64C 9/22 (2006.01)

Patent

CA 2682680

The invention provides an aircraft, comprising a fuselage (8), an airfoil (1) mounted to the fuselage (8) and a flap (2; 3) for steering the aircraft. Furthermore, connecting means (18; 79) articularly connect the flap (2; 3) to the airfoil (1) such that the flap (2; 3) is allowed to rotate around a rotation axis (28; 82) substantial parallel to the trailing or leading edge (4; 5) of the airfoil (1) between a retracted position (I) and an extended position (II) and to translate in a direction (54a; 98) substantially parallel to the rotation axis (28; 82). A rod (43; 95) articularly connect the flap (2; 3) to the airfoil (1) or to the fuselage (8), wherein the rod (43; 95) defines the translation of the flap (2; 3) in the direction (55a; 98) parallel to the rotation axis (28; 82). Hence, by way of the invention, forces acting of the flap (2; 3) in a direction (55a; 98) parallel to the rotation axis (28; 82) can be taken up by the rod (43; 95). Consequently, there is no need for using locating bearings having negative aerodynamic effects due to their by comparison large dimensions in a direction substantially perpendicular to the direction of flight (12) of the aircraft.

L'invention concerne un aéronef, comprenant un fuselage (8), une surface portante (1) montée sur le fuselage (8) et un volet (2; 3) pour diriger l'avion. En outre, des moyens de liaison (18; 79) relient de façon articulée le volet (2; 3) à la surface portante (1) de telle sorte que le volet (2; 3) peut tourner autour d'un axe de rotation (28; 82) sensiblement parallèle au bord de fuite ou d'attaque (4; 5) de la surface portante (1) entre une position escamotée (I) et une position étendue (II) et se déplacer dans une direction (54a; 98) sensiblement parallèle à l'axe de rotation (28; 82). Une tige (43; 84) relie de façon articulée le volet (2; 3) à la surface portante (1) ou au fuselage (8), la tige (43; 84) définissant la translation du volet (2; 3) dans la direction (55a; 98) parallèle à l'axe de rotation (28; 82). Par conséquent, grâce à l'invention, les forces agissant sur le volet (2; 3) dans une direction (55a; 98) parallèle à l'axe de rotation (28; 82) peuvent être absorbées par la tige (43; 95). En conséquence, il n'y a aucun besoin d'utiliser des paliers de positionnement ayant des effets aérodynamiques négatifs en raison de leurs dimensions comparativement grandes dans une direction sensiblement perpendiculaire à la direction de vol (12) de l'avion.

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