Patent ID: 6176679
Filing Date: 2001-01-23
Classification: B64C

Abstract:
Rotor with folding blades for the rotary wings of an aircraft, comprising a hub secured to one end of a rotor mast intended to be rotated about an axis of the rotor, and to which hub each blade of the rotor is connected by a connecting member which is substantially radial with respect to the axis of the rotor, said connecting member being connected to the hub by retaining and articulating means allowing angular excursions of the corresponding blade with respect to the hub at least in terms of pitch about a longitudinal pitch-change axis of the blade, each blade being mounted so that said blade can pivot with respect to the corresponding connecting member about an axis of folding, so that said blade can be moved, when the rotor is stopped, between two positions, one of which is a flight position, in which the blade is substantially radially in line with said connecting member, and the other of which is a folded position, in which the blade is pivoted about the axis of folding to one side of said connecting member towards the rear of the aircraft, wherein said axis of folding is in a substantially radial plane passing through the axis of the rotor and is inclined with respect to the axis of the rotor so that said axis of folding converges towards the axis of the rotor on the opposite side to the rotor mast.