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 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 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 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 load compensation device may include an assisted joint configured to be constrained to a support structure; a main rod comprising a proximal end connected to the assisted joint, and further comprising a distal end configured to be stressed by an applied load; an auxiliary rod comprising a first end and a second end, the first end being hinged on the main rod for rotating the auxiliary rod with respect to the main rod, the second end being movable on a plane on which the applied load lies; an elastic element configured to provide an elastic force which acts between the second end of the auxiliary rod and the distal end of the main rod; a regulation system configured to modify a distance between the second end of the auxiliary rod and the assisted joint, so as to vary a preloading of the elastic element.

Abstract: A rotor for an aircraft is described that comprises: 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 connected to the hub to drive the hub in rotation about the axis; and damping means to dampen the transmission of vibrations to the mast in a plane orthogonal to the axis; the damping means comprising at least a first mass and a second mass that can eccentrically rotate about the axis with a first and a second speed of rotation, respectively; the first mass and second mass are operatively connected to the mast to generate, respectively, a first and a second damping force on the mast having a main component in a direction radial to the axis; the rotor comprises a transmission unit, which is interposed between the mast and the first and second masses so as to drive the first and second masses in rotation.

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).

Abstract: A microelectromechanical transducer includes a semiconductor body having first and second surfaces opposite to one another. A plurality of trenches extend in the semiconductor body from the first surface towards the second surface, including a first pair of trenches having a respective main direction of extension along a first axis, and a second pair of trenches having a respective main direction of extension along a second axis orthogonal to the first axis. A first piezoresistive sensor and a second piezoresistive sensor extend at the first surface of the semiconductor body respectively arranged between the first and second pair of trenches. The first piezoresistive sensor, the second piezoresistive sensor and the plurality of trenches form an active region. A first structural body is mechanically coupled to the first surface of the semiconductor body to form a first sealed cavity which encloses the active region.

Abstract: A microelectromechanical force/pressure sensor has: a sensor die, of semiconductor material, having a front surface and a bottom surface, extending in a horizontal plane, and made of a compact bulk region having a thickness along a vertical direction, transverse to the horizontal plane; piezoresistive elements, integrated in the bulk region of the sensor die, at the front surface thereof; and a cap die, coupled above the sensor die, covering the piezoresistive elements, having a respective front surface and bottom surface, opposite to each other along the vertical direction, the bottom surface facing the front surface of the sensor die.

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: A microelectromechanical force/pressure sensor has: a sensor die, of semiconductor material, having a front surface and a bottom surface, extending in a horizontal plane, and made of a compact bulk region having a thickness along a vertical direction, transverse to the horizontal plane; piezoresistive elements, integrated in the bulk region of the sensor die, at the front surface thereof; and a cap die, coupled above the sensor die, covering the piezoresistive elements, having a respective front surface and bottom surface, opposite to each other along the vertical direction, the bottom surface facing the front surface of the sensor die.

Abstract: A MEMS gyroscope is equipped with: at least a first mobile mass suspended from the top of a substrate by means of elastic suspension elements coupled to anchor points rigidly fixed to the substrate, in such a manner as to be actuated in an actuating movement along a first axis of a horizontal plane and to carry out a measurement movement along a vertical axis, transverse to the horizontal plane, in response to a first angular velocity acting about a second axis of the horizontal plane, transverse to the first axis. The elastic suspension elements are configured in such a manner as to internally compensate unwanted displacements out of the horizontal plane along the vertical axis originating from the actuating movement, such that the mobile mass remains in the horizontal plane during the actuating movement.

Abstract: A microelectromechanical force/pressure sensor has: a sensor die, of semiconductor material, having a front surface and a bottom surface, extending in a horizontal plane, and made of a compact bulk region having a thickness along a vertical direction, transverse to the horizontal plane; piezoresistive elements, integrated in the bulk region of the sensor die, at the front surface thereof; and a cap die, coupled above the sensor die, covering the piezoresistive elements, having a respective front surface and bottom surface, opposite to each other along the vertical direction, the bottom surface facing the front surface of the sensor die.

Abstract: A rotor for an aircraft is described that comprises: 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 connected to the hub to drive the hub in rotation about the axis; and damping means to dampen the transmission of vibrations to the mast in a plane orthogonal to the axis; the damping means comprising at least a first mass and a second mass that can eccentrically rotate about the axis with a first and a second speed of rotation, respectively; the first mass and second mass are operatively connected to the mast to generate, respectively, a first and a second damping force on the mast having a main component in a direction radial to the axis; the rotor comprises a transmission unit, which is interposed between the mast and the first and second masses so as to drive the first and second masses in rotation.

Abstract: A microelectromechanical transducer includes a semiconductor body having first and second surfaces opposite to one another. A plurality of trenches extend in the semiconductor body from the first surface towards the second surface, including a first pair of trenches having a respective main direction of extension along a first axis, and a second pair of trenches having a respective main direction of extension along a second axis orthogonal to the first axis. A first piezoresistive sensor and a second piezoresistive sensor extend at the first surface of the semiconductor body respectively arranged between the first and second pair of trenches. The first piezoresistive sensor, the second piezoresistive sensor and the plurality of trenches form an active region. A first structural body is mechanically coupled to the first surface of the semiconductor body to form a first sealed cavity which encloses the active region.