Abstract: A rotor for an aircraft capable of hovering includes a stationary support structure and a rotative element, which is rotatable about a first axis with respect to said stationary support structure with a first rotational speed. The rotor includes at least one blade, which is operatively connected with said rotative element; and a transmission group, which includes an output element rotatable about first axis with a second rotational speed different from first rotational speed.

Abstract: A rotor for an aircraft capable of hovering includes a stationary support structure and a rotative element which is rotatable about an axis with respect to the stationary support structure. The rotor has at least one blade, which is operatively connected with a rotative element. The rotor has a source of a magnetic field, which is either stationary or driven in rotation at a first rotational speed and an electric conductive element, which is operatively connected to the rotative element and can be driven in rotation at a second rotational speed different from first rotational speed. An electric conductive element is electromagnetically coupled so that an electromotive force is magnetically induced in electric conductive element itself Two rings extend radially inward from a tubular body of the rotor hub with the first ring connected to a plurality of thermally conductive rings of a flow deflector at an axial end of the rotor and the second ring supports the electric conductive element.

Abstract: There is disclosed a rotor for an aircraft capable of hovering, comprising a stationary support structured; a rotative element, which is rotatable about an axis with respect to stationary support structure; at least one blade, which is operatively connected with rotative element; a source of a magnetic field, which is either stationary or driven in rotation at a first rotational speed; and an electric conductive element, which is operatively connected to rotative element and can be driven in rotation at a second rotational speed from first rotational speed; electric conductive element is electromagnetically coupled with source, so that an electromotive force is magnetically induced in electric conductive element itself, wherein two rings extend radially inward from a tubular body of the rotor hub, the first ring connecting to a plurality of thermally conductive rings of a flow deflector at an axial end of the rotor, the second ring supporting the electric conductive element.

Abstract: There is disclosed a rotor for an aircraft capable of hovering, comprising: a stationary support structure; a rotative element, which is rotatable about a first axis with respect to said stationary support structure with a first rotational speed; at least one blade, which is operatively connected with said rotative element; and a transmission group, which comprises an output element rotatable about first axis with a second rotational speed different from first rotational speed.