Abstract: A hover aircraft rotor having a hub which rotates about an axis and has a number of blades; a drive shaft connectable to a drive member of the aircraft and connected functionally to the hub to rotate the hub about the axis; and damping means for damping vibration transmitted to the shaft, and which include a mass designed to oscillate, in use, to oppose transmission to the shaft of vibration generated by rotation of the blades; the mass being free to oscillate parallel to the axis, to oppose transmission to the shaft of vibration having main components along the axis.

Abstract: A trim panel for the interior of an aircraft, the panel having a multilayer structure and including an outer layer made of material impervious to air, and which is positioned in use facing the fuselage of the aircraft; an inner layer made of trim material, and which in use defines the interior; a structural layer interposed between the inner and outer layer; and acoustic energy dissipating material, also interposed between the inner and outer layer; the inner layer being made of porous material allowing airflow towards the acoustic energy dissipating material.

Abstract: A real-time simulation system of the aerodynamic loads generated by the wake of a rotor of a hover-capable aircraft on the aircraft itself is described, said system comprising: a cockpit seat; a simulated control device able to receive a simulated command to simulate a flight condition of the aircraft; a plurality of simulation devices able to generate a simulated representation of the flight condition; and a processing unit configured to receive a first signal associated with the command given via the control device and to generate a second control signal for the plurality of simulation devices associated with the simulated aerodynamic loads. The processing unit cyclically generates a vortex ring, associates one or more control points with the vortex ring, computes the velocity induced on the control points, moves and updates the vortex ring, and generates the second signal on the basis of the velocities induced on the control points.

Abstract: An aircraft rotor blade having a root portion having a through seat and designed for connection to the rotor; and a main portion extending from the root portion. The blade is produced by polymerizing an assembly having a main structure of composite material, and a composite material covering defining the outer surface of the blade. At the root portion, the main structure has a contoured block; and a lamina member extending about at least part of the block, and having a first part adhering to a first peripheral portion of the block, and a second part spaced apart from and facing a second peripheral portion of the block to form the seat; the lamina member having a pre-preg of continuous unidirectional fibers.

Abstract: An insert made of electrically conducting material, insertable at least partly inside a seat on a first member, and connectable to a second member; the insert having a fastening member connectable electrically to a first electrically conducting area on the first member.

Abstract: A hover-capable aircraft having propulsion means; at least one rotor; transmission means for transmitting power from the propulsion means to the rotor and lubricated with a lubricant; a heat exchanger, which receives the heated lubricant from the transmission means and feeds the cooled lubricant back to the transmission means; and a fan for producing airflow through the heat exchanger to cool the lubricant, and which has an impeller with blades, and an exhaust pipe for expelling the hot air produced by cooling the lubricant; at least one portion of the wall of the exhaust pipe has dissipating means designed to selectively absorb pressure waves in a given frequency band related to the rotation speed of the impeller and to the number of blades of the impeller.

Abstract: 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.

Abstract: A constraint assembly for an aircraft, having a first member; a second member mounted to translate along and rotate about its own axis; and connecting means for connecting the first and second member, to prevent rotation of the second member about the axis with respect to the first member; the connecting means having a retaining arm, which projects outwards from one of the first and second member, and extends at a distance of other than zero from the axis; and an antirotation bracket, which projects from the other of the first and second member, extends at a distance of other than zero from the axis, and defines a through opening engaged in sliding manner by the retaining arm.

Abstract: A lock ring for securing a threaded stud to a first member, the ring having a first surface defining the ring on the side facing a first axis of symmetry of the ring, and in which a toothed impression is formed when it is forced onto a toothed portion of the threaded stud; and a conical second surface defining the ring on the opposite side to the first axis, and which is forced inside the first member.

Abstract: 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.

Abstract: An electronic flight control system for an aircraft capable of hovering and having at least one rotor. The flight control system is configured to operate in a manual flight control mode, in which the flight control system controls rotor speed in response to direct commands from the pilot; and in at least two automatic flight control modes corresponding to respective flight modes of the aircraft, and in which the flight control system controls rotor speed automatically on the basis of flight conditions. The flight control system is also configured to memorize, for each automatic flight control mode, a respective flight table relating different speed values of the rotor to different values of at least one flight quantity; and to automatically control rotor speed in the automatic flight control modes on the basis of the respective flight tables.

Abstract: An aircraft, capable of hovering, having drive means; and at least one exhaust duct connected to an outlet of the drive means to expel the exhaust gas, produced by fuel combustion, from the aircraft. At least part of the exhaust duct has a thermoelectric conversion circuit for Seebeck-effect converting to electric energy the thermal gradient produced between the inside and outside of the exhaust duct by flow of the exhaust gas.

Abstract: 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.

Abstract: A system for cooling a transmission of a hover-capable aircraft, the system having: a stator; a heat exchanger connectable thermally to the transmission; a fan for creating a current of a first heat-carrying fluid from the heat exchanger to the fan itself, to remove heat from the heat exchanger; a rotary member, which rotates about an axis to rotate an impeller of the fan about the axis; and a bearing supporting the rotary member for rotation about the axis; the system also having cooling means for cooling the bearing, and in turn having conducting means for conducting a current of a second heat-carrying fluid along a path from an outside environment, external to the bearing, to and to cool the bearing itself.

Abstract: A hover-capable aircraft having propulsion means; at least one rotor; transmission means for transmitting power from the propulsion means to the rotor and lubricated with a lubricant; a heat exchanger, which receives the heated lubricant from the transmission means and feeds the cooled lubricant back to the transmission means; and a fan for producing airflow through the heat exchanger to cool the lubricant, and which has an impeller with blades, and an exhaust pipe for expelling the hot air produced by cooling the lubricant; at least one portion of the wall of the exhaust pipe has dissipating means designed to selectively absorb pressure waves in a given frequency band related to the rotation speed of the impeller and to the number of blades of the impeller.

Abstract: A fastening assembly having a tubular first coupling member; a second coupling member insertable coaxially inside the first coupling member in a first direction; and releasable fastening means for locking the first and second coupling member to each other in a predetermined axial lock position. The fastening means include: first and second engaging means formed on the first and second coupling member, connectable to each other to define a foolproof angular insertion/release position, and releasable by positioning the second coupling member in a predetermined axial position inside the first coupling member; and third and fourth engaging means formed on the first and second coupling member and connectable to each other in a further angular position of the second coupling member, different from the angular insertion/release position, by moving the second coupling member axially, from the predetermined axial position, in a second direction opposite the first direction.

Abstract: An epicyclic gear train, for an aircraft capable of hovering, having a sun gear rotating about a first axis; a fixed ring gear positioned coaxially with the first axis and radially outwards with respect to the sun gear; a number of planet gears, which are interposed between and mesh with the sun gear and the ring gear, and rotate about respective second axes, in turn revolving about the first axis; and lubricant feed means; the feed means having a number of nozzles arranged about the first axis and the sun gear to produce an annular flow of lubricant.

Abstract: An aircraft rotor blade having a root portion having a through seat and designed for connection to the rotor; and a main portion extending from the root portion. The blade is produced by polymerizing an assembly having a main structure of composite material, and a composite material covering defining the outer surface of the blade. At the root portion, the main structure has a contoured block; and a lamina member extending about at least part of the block, and having a first part adhering to a first peripheral portion of the block, and a second part spaced apart from and facing a second peripheral portion of the block to form the seat; the lamina member having a pre-preg of continuous unidirectional fibres.

Abstract: 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.