Agustawestland S.p.a.

Leonardo S.p.a.

James Wang

Luigi Maria Bottasso

Luca Medici

Massimo Brunetti

Giorgio Lucchi

Antonio Zocchi

Luigi Bottasso

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.

Transmission for rotor for an aircraft capable of hovering

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.

Rotor for an aircraft capable of hovering

An anti-torque rotor of a helicopter, having: a supporting body; a drive shaft which rotates about a first axis with respect to the supporting body; a hub connected operatively to drive shaft and angularly fixed with respect to first axis; at least one blade which is connected operatively to hub, is angularly fixed with respect to first axis, and is angularly movable with respect to a second axis to adjust the pitch angle of blade; and an actuator which can be operated to rotate blade about second axis to adjust the pitch angle of blade; actuator has an electric motor which generates torque along the first axis; and a mechanical stage interposed between the electric motor and blade, and designed to convert the torque into rotation of blade about the respective second axes; electric motor is fixed to supporting body.

Helicopter anti-torque rotor

There is described a convertiplane comprising: a pair of semi-wings; a first rotor comprising a shaft which may rotate about first axis and tilt about a second axis together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being transversal to a longitudinal direction of convertiplane in helicopter mode and being substantially parallel to longitudinal direction in aeroplane mode; convertiplane also comprises an electrical power storage device; and an electrical machine which comprises, in turn: a stator electrically connected to storage device; and a second rotor operatively connected to a shaft of first rotor; electrical machine acts as an electric motor for driving in rotation said first rotor by using the electrical power stored in storage device; or as an electrical power generator for re-charging storage device by causing the rotation second rotor under the action of a wind current.

Convertiplane

Tilt-rotor

There is described a convertiplane comprising: a pair of semi-wings; at least two rotors which may rotate about relative first axes and tilt about relative second axes together with first axis with respect to semi-wings between a helicopter mode and an aeroplane mode; first axis being, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and being, in use, substantially parallel to longitudinal direction in aeroplane mode; convertiplane further comprises at least two through openings within which said rotor may tilt, when said convertiplane moves, in use, between said helicopter and said aeroplane mode.

There is described an aircraft, comprising a windscreen arranged in a front side of aircraft, characterized in that an edge of windscreen defines a visualization area visible by an operator, and by comprising displaying means configured for displaying at least one visual information of at least one flight parameter within visualization area, at least when aircraft is in a normal flight configuration.

Aircraft and method for displaying a visual information associated to flight parameters to an operator of an aircraft

There is described a convertiplane comprising a pair of semi-wings, a first and a second rotor which may rotate about relative first axes and tilt about relative second axes together with first axes with respect to semi-wings between a helicopter mode and an aeroplane mode; first axes are, in use, transversal to a longitudinal direction of convertiplane in helicopter mode, and are, in use, substantially parallel to longitudinal direction in aeroplane mode; first and second rotors may tilt about relative second axes independently of each other.

Growing community of inventors

Samarate, Italy

James Wang