Patent ID: 6729583
Filing Date: 2004-05-04
Classification: B64C,Y02T

Abstract:
A device for articulating a flap to an aircraft aerodynamic surface, said flap having its front edge facing a rear edge of said aerodynamic surface and said articulation device comprising at least two fittings bearing said flap projecting forward with respect to said front edge and able to pivot, under the action of actuating means, about a common axle borne by said aerodynamic surface and arranged at the interior side thereof, in order to cause said flap to adopt:either a retracted position, for which the outer face of said flap is in the aerodynamic continuation of the outer face of said aerodynamic surface; or at least one deployed position, for which said flap is turned and projects with respect to the outer face of said aerodynamic surface, said rear edge of said aerodynamic surface comprising cutouts into which said fittings project when said flap is in the deployed position, wherein: the portion of each fitting facing the corresponding cutout when said flap is in the retracted position is set back toward the inside with respect to the outer faces of the aerodynamic surface and of the flap; a flat blanking piece, the shape of which corresponds to that of said cutout is associated with each cutout; each blanking piece is borne by a linkage articulated to said aerodynamic surface and to said flap so that: when said flap is in the retracted position, said linkage places said blanking piece in a blanking position for which said blanking piece is arranged in said cutout, ensuring aerodynamic continuity between said aerodynamic surface and said flap; and when said flap is in the deployed position, said linkage places said blanking piece in an outwardly offset position for which said blanking piece uncovers said cutout, allowing said flap to turn with respect to said aerodynamic surface.