Patent ID: 10926863

Abstract:
Describes a deflection mechanism of the flap panels of an aircraft, the aforesaid deflection mechanism being connected to a wing of an aircraft by means of a first fixed structure and to the flap panels by linkage points, in order to support and deflect the flap panels in desired positions, the deflection mechanism of the flap panels of an aircraft comprises of a set of moving hinged links pivotally connected with each other and linked to a first fixed structure, and a hinged drive link connected to the flap panel and to a second fixed structure, the set of moving hinged links being linked to the flap panel by at least one linkage point in order to pivot jointly the moving hinged links deploying the flap panels in an initially predominantly rectilinear and subsequently deflected trajectory and at the same time aligned with a longitudinal direction of the aircraft, without the use of tracks and rollers, the hinged drive link being pivoted from the movement of the flap panels by the set of moving hinged links.