Leonardo S.p.a.

Politecnico Di Milano

Giuseppe Quaranta

Luigi Maria Bottasso

Attilio Colombo

Pierangelo Masarati

Aykut Tamer

Federico Savorgnan

Garbo Pierre

Alberto Lavatelli

A rotor for a hover-capable aircraft is described, comprising: a hub rotatable about an axis and, in turn, comprising a plurality of blades; a mast connectable to a drive member of the aircraft and operatively connected to the hub to drive the hub in rotation about the axis; and damping means for damping vibrations transmitted to the mast, which comprise a mass designed to oscillate in a plane transversal to the axis so as to contain flexural vibrations of the mast generated by rotation of the blades; the damping means also comprise elastic means having a desired stiffness along the axis and operatively connected to the mass to contain vibration of the mast along the axis.

Rotor for a hover-capable aircraft and method for containment of vibrations transmitted to the mast of a rotor of a hover-capable aircraft

A kit for a helicopter is described, the helicopter comprising a fuselage and a rotor; the kit comprises at least one device adapted to dampen the vibrations transmitted from the rotor to the fuselage and to be interposed between the fuselage and the rotor; the device, in turn, comprises a first threaded element operatively connectable to the rotor and adapted to, in use, vibrate parallel to a first axis; a second threaded element operatively connectable to the fuselage and operatively connected to the first threaded element so as to, in use, rotationally vibrate about the first axis; and a plurality of threaded rollers, which are screwed on the first and second threaded elements; the rollers being rotatable about their respective second axes parallel to and separate from the first axis with respect to the first and second threaded elements; the rollers are also rotatable about the first axis with respect to the first threaded element and the second threaded element.

Helicopter kit

A kit is described that comprises a device adapted to dampen the vibrations transmitted by the rotor to the fuselage; the device comprises two first elements movable along a first axis; two second elements rotatable about the first axis; a first inerter with a first female screw, a first screw, and first rollers rotatable about respective second axes and around the first axis with respect to the first female screw and first screw; a second inerter with a second female screw, a second screw operatively connected to the second female screw; and a plurality of second rollers rotatable about second axes and around the first axis with respect to the second female screw and second screw; the first and second female screws defining the first threaded elements, and the first and second screws defining the second threaded elements; or the first and second screws defining the first threaded elements and the first and second female screws defining the second threaded elements.

Growing community of inventors

Samarate, Italy

Giuseppe Quaranta