Lift rotor and vertical or short take-off and/or landing hybrid aerodyne comprising same

A rotor for a hybrid aerodyne having a fuselage with a roll axis and provided with a fixed wing and a rotary wing configured for being held stationary in cruising flight of the aerodyne, the rotor having a radius R and configured for producing lift by rotating around a mast axis during a stage of vertical flight and for being held stationary and stored longitudinally during a stage of cruising flight, the rotor comprising at least one single-blade with a counterweight being rotatable around a rotor axis, said at least one single-blade comprising:

• an active blade that generates the lift of the rotor during rotation;
• a first portion that carries said active blade and that constitutes a connection between the active blade and a rotor mast;
• and
• a second portion that carries said counterweight and that constitutes a connection between the counterweight and said rotor mast,
• said active blade having a length along its span direction which is less than said radius R of the rotor;
• said first portion carrying the active blade being a portion that is structurally rigid;
• said first portion having a cross-section of aerodynamic profile providing zero or almost zero lift when the rotor is in rotation;
• said first portion and said active blade being constituted as an assembly;
• wherein said assembly having a common longitudinal axis, is hinged about a transverse axis perpendicular to the mast axis, and to the common longitudinal axis, the transverse axis crossing the mast axis;
• wherein the rotor comprises at least two of the at least one single-blade that are identical and rotate in opposite directions, each single-blade rotating about a respective one of axes of rotation that are longitudinally spaced apart along the roll axis of the fuselage;
• and
• wherein during cruising flight, each single-blade is stopped and locked longitudinally and horizontally, and the at least two of the single-blades are aligned along an axis parallel to the roll axis of said fuselage and that the counterweight of each single blade is oriented towards the front of the aerodyne and the active blade is oriented towards the rear of the aerodyne, substantially in the direction of the roll axis of the aerodyne, and that, during vertical flight, the at least two of the single-blades rotate in opposite directions at the same angular speed from an initial zero position, which is said longitudinally and horizontally stopped position.