Abstract: Method implemented through a computer for detecting the execution, by an aircraft, of a manoeuvre belonging to a macrocategory among a plurality of macrocategories, including: receiving a data structure with a plurality of time series of values of quantities relating to a flight of the aircraft; for each time duration among a plurality of predetermined time durations, selecting a corresponding subset of the data structure and extracting a corresponding feature vector; on the basis of the feature vectors, generating a corresponding input macrovector and applying to the input macrovector an output classifier to generate estimates indicative of the probability that the aircraft was performing manoeuvres belonging to the macrocategories.

Abstract: Braking device inserted in a test bench (2) for checking the correct operation of industrial screwdrivers, wherein the braking simulates a tightening operation of such screwdriver, comprising a container body (1) on the top of which a coupling (11) protrudes, suitable for coupling with the head (3) of the screwdriver to be tested, said coupling (11) being connected, by means of a shaft (12), to a braking unit (13), an electronic torque and angle detector (14) of the shaft rotation (12). Such braking unit (13) comprises a plate (14), rotated by the screwdriver, which is braked by suitable friction surfaces (15) moved towards the plate by the movement of an actuator; the movement of such actuator is performed by means of at least one electronically controlled piezoelectric element (17).

Abstract: A rotor for a hover-capable aircraft includes an attenuating device to attenuate the transmission of vibrations from a mast to the aircraft. The attenuating device includes a first mass free to oscillate parallel to a hub rotation axis with respect to a casing of the attenuating device and elastically connected to the casing. The attenuating device further includes a second mass free to oscillate parallel to the hub rotation axis, connection means adapted to make the first and second masses integrally movable along the hub rotation axis when the angular speed of the mast assumes a first value, and actuator means activatable to decouple the first and second masses when the angular speed of the mast assumes a second value, different from the first value.

Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis; and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses; and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and each control unit comprises: a belt coupled to the support assembly and a drive unit coupled to the first belt, to cause the rotation of the first support assembly with respect to said transmission device.

Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis, and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses, and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and comprises a set of drive gear teeth integral with the first support assembly, a cogwheel with a set of control gear teeth meshing with the drive gear teeth, and an actuator to cause the rotation of the cogwheel about a second axis and of the first mass about said first axis.

Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis, and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses, and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and comprises a set of drive gear teeth integral with the first support assembly, a cogwheel with a set of control gear teeth meshing with the drive gear teeth, and an actuator to cause the rotation of the cogwheel about a second axis and of the first mass about said first axis.

Abstract: A rotor for a hover-capable aircraft is described that comprises: a hub rotating about an axis and, in turn, comprising a plurality of blades, a mast connectable to a power unit of the aircraft and operatively connected to the hub to drive the hub in rotation about said axis, and an attenuating device to attenuate the transmission of vibrations from the mast to the aircraft parallel to said; the attenuating device, in turn, comprising a casing, a first mass free to oscillate parallel to said axis with respect to the casing and elastically connected to the casing, a second mass free to oscillate parallel to said axis, connection means adapted to make the first and second masses integrally movable along said axis when the angular speed of the mast assumes a first value, and actuator means activatable to decouple the first and second masses when the angular speed of the mast assumes a second value, different from the first value.

Abstract: A rotor for an aircraft is described that has a mast, an attenuating device to attenuate the transmission of vibrations from the mast in a plane orthogonal to the first axis; and a transmission device interposed between the mast and the attenuating device; the attenuating device comprises a first and a second mass unit with a first and a second mass rotatable about the first axis with a first and a second rotational speed, two control units operable to cause an additional rotation of at least one of the first and second masses and a first and a second support assembly carrying the first and second masses; each control unit controls the angle between the first and second masses and each control unit comprises: a belt coupled to the support assembly and a drive unit coupled to the first belt, to cause the rotation of the first support assembly with respect to said transmission device.

Abstract: A system for verifying proper functioning of industrial screwdrivers placed on a test bench is provided. The bench includes a plurality of hydraulic brakes, with which the screwdriver is associated, controlled by a hydraulic circuit including a pump, which withdraws the fluid from a reservoir and provides it to a pressure regulating valve, which in turn provides it to the brakes. Each brake is provided with measuring transducers connected to an electronic driver board, which also controls the regulating valve. A hydraulic distributor is present between the brakes and the regulating valve, the hydraulic distributor including solenoid valves able to select, operate and control the hydraulic pressure of each brake to which it is selectively connected. A computer communicates with the board and includes a driving program stored thereon capable of progressively increasing the braking capacity of the brakes according to a preset braking torque/brake rotation angle curve.

Abstract: Braking device inserted in a test bench (2) for checking the correct operation of industrial screwdrivers, wherein the braking simulates a tightening operation of such screwdriver, comprising a container body (1) on the top of which a coupling (11) protrudes, suitable for coupling with the head (3) of the screwdriver to be tested, said coupling (11) being connected, by means of a shaft (12), to a braking unit (13), an electronic torque and angle detector (14) of the shaft rotation (12). Such braking unit (13) comprises a plate (14), rotated by the screwdriver, which is braked by suitable friction surfaces (15) moved towards the plate by the movement of an actuator; the movement of such actuator is performed by means of at least one electronically controlled piezoelectric element (17).