Abstract: A centrifugal gas-liquid separator wherein a tubular casing houses a central tubular duct, which is provided with a first free end and with a second end that communicates with a gas-outlet duct and carries a transversal annulus-shaped plate having a perimetral edge that faces the inner wall of the tubular body to define an annular gap. The plate divides the space inside the tubular casing into a first chamber and into a second chamber that communicate with each other through the annular gap. A liquid-outlet duct communicates with the second chamber and a liquid-phase/gas-phase inlet duct extends tangentially from the tubular casing and discharges into the first chamber through an inlet nozzle. A regulation device is provided, which is designed to modify the section of the inlet nozzle in order to modify the rate of entry of the liquid phase and gas phase into the first chamber and to adapt the operation of the centrifugal gas-liquid separator following variations of flow rate.

Abstract: An ice-breaking system for an aircraft, comprising a pneumatic ice-breaking device, an air inlet adapted to receive air from the environment outside the aircraft and an air outlet adapted to discharge air into the outside environment, and a motorized valve having an air loading port connected to the air inlet and an air discharge port connected to the air outlet, the valve being configured to supply air to the pneumatic ice-breaking device in a pulsating way. When the aircraft is in motion, the kinetic energy of the air at the air inlet and originating from the relative motion between the air and the aircraft is converted into air pressure at the pneumatic ice-breaking device, and the air outlet is positioned so that when the aircraft is in motion the air pressure at the air outlet is lower than the outside ambient pressure.

Abstract: 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.

Abstract: A method for manufacturing a wing-box for aircraft comprises: arranging, on a curing surface, a first panel of composite material comprising a skin a plurality of longitudinal stringers, and arranging, on each stringer, a caul plate; arranging, on the first panel, pluralities of support inserts so that each support insert rests on a respective caul plate, and on the skin of the first panel, and arranging, on the first panel, a plurality of ribs of non-polymerized composite material, each rib comprising a plate, a first pair of flanges and a second pair of flanges arranged at opposed ends of the plate, and having openings on an edge of the plate, by placing the respective first pair of flanges on the first panel and the respective plurality of openings on the plurality of support inserts, and having the first panel and the plurality of ribs undergo a curing process in autoclave with vacuum bag.

Abstract: A rotor for a hover-capable aircraft includes a hub rotatable about a first axis and at least two blades hinged to the hub. Each blade has a main portion hinged to the hub and a tip portion, which is arranged radially outermost with respect to first axis with respect to the corresponding main portion. The tip portion of each blade is movable with respect to the corresponding main portion of that blade. The tip portion of each blade is selectively movable with respect to the corresponding main portion of that blade between a first position, in which it defines a dihedral or anhedral angle with respect to the corresponding main portion; and a second position, in which it defines a positive or negative sweep angle with respect to the corresponding main portion.

Abstract: Described herein is a safety valve for a hydraulic circuit comprising a pump designed to supply a hydraulic fluid at a first pressure value to a pressure line, comprising: a chamber, which can be fluidically connected to the pressure line and is filled with the hydraulic fluid at a pressure value and a temperature value; and a casing with an opening, which can be connected to a reservoir of the hydraulic circuit; a shutter, which delimits the first chamber and can be displaced between a first position, in which it occludes the first opening, and a second position, in which it leaves the opening at least in part free; the valve comprises a thermally expandable element, which can be displaced, as a result of the temperature of the hydraulic fluid, between a first configuration that it assumes when the temperature of the hydraulic fluid is below the threshold value and a second configuration that it assumes when the temperature of the hydraulic fluid is above the temperature threshold value and in which it holds

Abstract: A damping device is described that is designed to counter the transmission of vibrations to a further element and comprises: a beam element, which extends mainly parallel to an axis, is constrained to the further element and is designed to flexurally oscillate, in use, in a plane parallel to the axis to counter the transmission of vibrations to the further element; an actuator, which comprises a transmission element operatively connected to the beam element and extending mainly along the axis; the actuator being controllable to apply a direct tensile or compressive load along the axis on the transmission element that is variable according to the frequency of the vibrations to be dampened.

Abstract: A turret includes a firearm, which is configured to shoot munitions. A support assembly supports the firearm and is configured to move the firearm about an azimuthal rotation or swiveling axis (Y) and about a zenithal rotation or elevation axis (X). A munition guidance device mounts on the support assembly and is configured to direct a precision-guided munition, which is shot by the firearm towards a target. A protection apparatus is mounted on the support assembly and is configured to assume: a covering condition, in which the protection apparatus hides the munition guidance device on the inside of the support assembly; and an opening condition, in which the protection apparatus exposes the munition guidance device on the outside of the support assembly.

Abstract: Non-destructive inspection device, comprising: a first structural layer; a second structural layer coupled to the first structural layer; a chamber sealed between the first and second structural layers, containing a gas; and an active region, housed in the chamber, of a Graphene-based material. In a first operating condition, an AC electric current is fed to the active region and generates by thermoacoustic effect a first acoustic wave propagating away from the chamber. In a second operating condition, a second acoustic wave, generated by a reflection of the first acoustic wave, is received at the chamber and causes a variation in pressure and, consequently, a variation in the temperature of the gas contained in the chamber generating, by means of the thermoelectric effect, an electrical signal in the active region.

Abstract: A rotor for a hover-capable aircraft is described that comprises: a drive mast; a hub operatively connected to the drive mast and rotatable about a first axis; and at least two blades hinged to the hub, via a rigid or elastically deformable connection, so as to be able to assume an attitude rotated about and/or translated along at least a second axis with respect to said hub; the aircraft further comprising sensor means configured to detect the attitude of at least one said blade with respect to the hub; the sensor means are configured to acquire an optical image associated with the attitude of the blade with respect to the hub.

Abstract: The connection device comprises two thermal expansion valves releasably connected directly to each other, each valve being configured to be mounted to an end of a respective section of a fluid circuit and being shiftable between an open position and a closed position, in which it allows and prevents fluid flow through the device, respectively, depending on the fluid temperature.

Abstract: An avionics system comprising a central processing unit to implement one or more hard real-time safety-critical applications, the central processing unit comprises a multi-core processor with a plurality of cores, an avionics system software executable by the multi-core processor, a memory, and a common bus though which the multi-core processor can access the memory; the avionics system is characterized in that the avionics system software is designed to cause, when executed, the cores in the multi-core processor to access the memory through the common bus by sharing bus bandwidth according to assigned bus bandwidth shares.

Abstract: A wheel drive cart for a transporting and/or sorting system configured to tow a plurality of loading carts movable along a closed path, constituted by a first and a second rail parallel to each other, between a loading and unloading stations. The cart includes a pair of direct drive wheels without reducers, with each wheel including an electric motor having a stator, integral with a bracket hinged to a frame of the cart, and a rotor, a peripheral outward facing portion of which forms a cylindrical surface of the wheel designed to roll on a resting surface of a respective rail.

Abstract: A fuze for an explosive weapon, comprising onboard sensors to monitor operation of the fuze and/or the explosive weapon, a radar sensor to transmit radar signals and receive reflected radar signals, and an electronic signal processor connected to the onboard sensors and to the radar sensor and programmed to implement a main operating function aimed at implementing a detonation logic, and a secondary operating function supplemental to the main one and comprising a telemetry function designed to determine, based on signals from the onboard sensors, and to transmit, via the radar sensor, telemetry data indicative of the operation of the fuze and/or the explosive weapon during flight thereof.

Abstract: A covering element is adapted to protect a paint-sensitive area wherein at least one opening is defined. The element includes a central stem having a distal portion intended to go through the opening, and a cap peripherally extending from a proximal portion of the central stem, for covering the area.

Abstract: A display device for displaying the attitude of an aircraft with respect to a fixed direction in space is described, said device comprising: a first element that can be fastened to the aircraft; and a second element, which is free to move with respect to the first element, following a change in position of first element with respect to the fixed direction; the second element in turn comprising: a mass, which is designed to return the second element to the same stable position with respect to the fixed direction when the first element changes its position with respect to the fixed direction; and a visual indication, which is representative of the position of the fixed direction, as the position of the first element changes.

Abstract: A helicopter is described that comprises: a rotor; a fuselage; a drive transmission unit operatively connected to the rotor; a support body, which supports the transmission unit; and constraining means interposed between the support body and the fuselage; the constraining means in turn comprise a crosspiece connected in a fixed manner with respect to the support body and having a first lying plane; the crosspiece is formed in part by a metallic material and in part by a visco-elastic material.

Abstract: Method for manufacturing stiffened panels comprising the following steps: forming a first and a second wet skin, each comprising a plurality of plies of preimpregnated composite material; forming a plurality of pairs of wet stringers, comprising a plurality of plies of preimpregnated material, wherein forming each pair of wet stringers comprises a) forming an assembly having a central web extending between opposite end flanges, and b) cutting the assembly along a median plane so as to form a pair of wet stringers, placing the pairs of wet stringers on the first wet skin by means of removable supporting members; turning the second wet skin over and placing it on the pairs of stringers, so as to obtain a pair of wet panels arranged above each other; and subjecting the pair of wet panels to a same curing cycle.