Abstract: A convertiplane having a fuselage with a first axis; and two rotors having respective shafts and fitted to a wing having a fixed portion connected to the fuselage, and a movable portion which supports the rotors, is connected to the fixed portion to rotate about a second axis crosswise to the first axis and to the shafts of the rotors, and is formed in one piece defined by two half-wings located on opposite sides of the fixed portion and each supporting a respective rotor, and by an elongated member extending along the whole wing and connecting the two half-wings; the rotors being powered by a motor via a transmission comprising a transmission shaft connecting the shafts of the rotors and coaxial with the second axis.

Abstract: A rotor for a helicopter, having: a hub rotating about an axis and in turn having a number of blades; and an at least partly hollow drive shaft connectable to a drive of the helicopter and connected functionally to the hub to rotate the hub about the axis; the rotor also having vibration damping means in turn having a mass, and an elastically deformable member connected to the mass and supported by the shaft; the member extending at least partly inside the shaft, and being elongated parallel to the axis; and the mass vibrating, in use, at such a frequency as to oppose transmission to the shaft of the vibration produced by rotation of the hub and blades.

Abstract: A wing for an aircraft having at least one weapon, and a feed duct for feeding the weapon with ammunition supplied in the form of a belt; the wing has a compartment for housing a portion of the belt and connectable to a loading opening of the feed duct.

Abstract: An aircraft capable of hovering, and having a fuselage defining an access opening; driving means for operating a rescue cradle; and a first wall movable between a closed position engaging a first portion of the opening, and a first open position allowing access to the first portion of the opening. The aircraft has a member connected functionally to the first wall and in turn having at least one flat surface; and the member is movable with respect to the wall into a first position, in which the flat surface defines a supporting surface for the cradle when the first wall is in the first open position.

Abstract: A convertiplane having a fuselage with a first axis; and two rotors having respective shafts and fitted to a wing having a fixed portion connected to the fuselage, and a movable portion which supports the rotors, is connected to the fixed portion to rotate about a second axis crosswise to the first axis and to the shafts of the rotors, and is formed in one piece defined by two half-wings located on opposite sides of the fixed portion and each supporting a respective rotor, and by an elongated member extending along the whole wing and connecting the two half-wings; the rotors being powered by a motor via a transmission comprising a transmission shaft connecting the shafts of the rotors and coaxial with the second axis.

Abstract: A helicopter having a rotor, a fuselage, and a transmission connected functionally to the rotor; the helicopter has a supporting body supporting at least the transmission, and connecting means having a first connecting member and at least one second connecting member connected to the supporting body and the fuselage respectively; and the connecting means have elastic means interposed between the first and second connecting member.

Abstract: An aircraft capable of hovering, and having a fuselage in turn having a nose, a tail portion at the opposite end to the nose, and a cabin interposed between the nose and the tail portion; the cabin has a loading opening at the opposite end to the nose, and a first wall movable between a closed position engaging at least one portion of the loading opening, and an open position allowing free access to the portion of the loading opening; and, working from the tail portion towards the nose, the first wall in the open position extends on the opposite side of a first edge of the loading opening with respect to a second edge, opposite the first edge, of the loading opening.

Abstract: An aircraft capable of hovering, and having a fuselage in turn having a nose, a tail portion at the opposite end to the nose, and a cabin interposed between the nose and the tail portion; the cabin has a loading opening at the opposite end to the nose, and a first wall movable between a closed position engaging at least one portion of the loading opening, and an open position allowing free access to the portion of the loading opening; and, working from the tail portion towards the nose, the first wall in the open position extends on the opposite side of a first edge of the loading opening with respect to a second edge, opposite the first edge, of the loading opening.

Abstract: A helicopter having a rotor, a fuselage connected to the rotor by connecting means, and a control device for controlling vibration of the fuselage; the control device including generating means for generating signals associated with vibration of the fuselage, and actuating means for producing a force on the fuselage associated with the signals to reduce vibration; and the actuating means being carried by the connecting means.

Abstract: There is described a rotor for a helicopter, having a hub rotating about a first axis; a number of blades projecting from the hub in respective longitudinal directions lying in a plane crosswise to the first axis, and each connected to the hub so as to be movable at least about a second axis crosswise to the first axis and to the relative longitudinal direction; and a number of damping devices for damping vibration of the helicopter, each interposed between a respective blade and the hub; each damping device has a plate member fixed, on one side, to the hub, elastically connected, on the opposite side, to the relative blade, and flexible, during movement of the blade, about a third axis coaxial with the second axis.

Abstract: A rotor for a helicopter, having: a hub rotating about an axis and in turn having a number of blades; and an at least partly hollow drive shaft connectable to a drive of the helicopter and connected functionally to the hub to rotate the hub about the axis; the rotor also having vibration damping means in turn having a mass, and an elastically deformable member connected to the mass and supported by the shaft; the member extending at least partly inside the shaft, and being elongated parallel to the axis; and the mass vibrating, in use, at such a frequency as to oppose transmission to the shaft of the vibration produced by rotation of the hub and blades.

Abstract: A helicopter having a rotor, a fuselage, and a transmission connected functionally to the rotor; the helicopter has a supporting body supporting at least the transmission, and connecting means having a first connecting member and at least one second connecting member connected to the supporting body and the fuselage respectively; and the connecting means have elastic means interposed between the first and second connecting member.

Abstract: An aircraft capable of hovering, and having a fuselage defining an access opening; driving means for operating a rescue cradle; and a first wall movable between a closed position engaging a first portion of the opening, and a first open position allowing access to the first portion of the opening. The aircraft has a member connected functionally to the first wall and in turn having at least one flat surface; and the member is movable with respect to the wall into a first position, in which the flat surface defines a supporting surface for the cradle when the first wall is in the first open position.

Abstract: A wing for an aircraft having at least one weapon, and a feed duct for feeding the weapon with ammunition supplied in the form of a belt; the wing has a compartment for housing a portion of the belt and connectable to a loading opening of the feed duct.

Abstract: A helicopter having a rotor, a fuselage connected to the rotor by connecting means, and a control device for controlling vibration of the fuselage; the control device including generating means for generating signals associated with vibration of the fuselage, and actuating means for producing a force on the fuselage associated with the signals to reduce vibration; and the actuating means being carried by the connecting means.

Abstract: There is described a rotor for a helicopter, having a hub rotating about a first axis; a number of blades projecting from the hub in respective longitudinal directions lying in a plane crosswise to the first axis, and each connected to the hub so as to be movable at least about a second axis crosswise to the first axis and to the relative longitudinal direction; and a number of damping devices for damping vibration of the helicopter, and each interposed between a respective blade and the hub; each damping device has a plate member fixed, on one side, to the hub, connected, on the opposite side, to the relative blade by elastic means, and flexible, during movement of the blade, about a third axis coaxial with the second axis.

Abstract: A helicopter having a fuselage; and two rear wings located on opposite sides of the fuselage and having winglets, each projecting transversely from a free end of the relative wing.

Abstract: There is described a hub for a helicopter rotor, having a main body, and a number of connecting members projecting from the main body and for the connection of respective blades; the main body and the connecting members being defined by separate components connectable to one another by releasable fastening means.

Abstract: There is described a hub for a helicopter rotor, having a main body, and a number of connecting members projecting from the main body and for the connection of respective blades; the main body and the connecting members being defined by separate components connectable to one another by releasable fastening means.

Abstract: An undercarriage for a helicopter, having a supporting structure connectable to the fuselage of the helicopter, a wheel suspended from the supporting structure, and a shock absorbing member which has a bottom end portion hinged to the wheel, and is interposed, in use, between the wheel and the fuselage. The supporting structure has an attachment fixable to the fuselage, and a first and a second beam having first connecting portions hinged about a first axis to each other and to a top end portion of the shock absorbing member. Second connecting portions are connected to separate portions of the attachment in articulated manner and lower down with respect to the first connecting portions.