Abstract: An attitude control and thrust boosting system (100) for a space launcher is disclosed, wherein the space launcher is equipped with a rocket engine (303) provided with an exhaust nozzle. The exhaust nozzle comprises a divergent portion (302) so designed as to make a supersonic gas flow exit through an exit section defined by a given angle of divergence with respect to a longitudinal axis of the rocket engine. The attitude control and thrust boosting system (100) comprises flaps (110, 111, 112, 113) that are arranged around the exit section, are shaped so as to extend the divergent portion of the exhaust nozzle, are mechanically decoupled from said exhaust nozzle and can be actuated to take different angular positions with respect to the longitudinal axis of the rocket engine.

Abstract: An inner coating layer for solid-propellant rocket engines, constituted by a material comprising from 45% to 55% wt. of a a cross-linkable, unsaturated-chain polymer base, from 11% to 13% wt. of silica, from 15% to 25% wt. of vulcanizing agents and plasticizers, from 5% to 7% wt. of aramid fiber and from 10% to 15% wt. of microspheres made of a material selected among glass, quartz and nano clay, having diameter lower than 200 ?m, density comprised between 0.30 and 0.34 g/cc and resistance to hydrostatic pressure greater than, or equal to, 4500 psi.

Abstract: A solid-propellant rocket engine (1) has a casing (2) and a thermal protection (15) internally coating the casing and delimiting a housing (17), which contains a mass of solid propellant (3); the thermal protection has a fixed portion (22) and at least one movable portion (23) that adheres to the mass of solid propellant (3) and can be moved from a back position to a forward position with respect to the fixed portion (22) through a thrust system obtained by pressuring a chamber 31 provided by installing a membrane 32 between the fixed portion 22 and the movable portion 23; the engine is tested by verifying the adhesion of the mass of solid propellant (3) to the movable portion (23) after having moved the movable portion (23) to the forward position by means of a thrust directed from the fixed portion towards the mass of solid propellant (3).

Abstract: For producing a dome-shaped element (2) provided with thermal protection for a solid propellant rocket engine, a coupling annular body (4) is arranged in a mold (5) and has a surface (20) that is clean and activated, by an atmospheric-pressure plasma treatment, before depositing a primer layer (26) and an adhesive layer (27) on the surface (20); ablative material is then automatically applied to the adhesive layer and to an area (17) of the mold (5) so as to form a series of superimposed layers (30).

Abstract: A solid propellant rocket motor has a tubular casing accommodating a mass of solid propellant material and at least one opening for the space in the casing to communicate with the outside closed by a closing head; the closing head being coupled to the casing by means of one or the other of two blocking portions with different strength both carried by a movement device which can be elastically deformed and operated from the outside.

Abstract: In a machine for forming a hollow body, for example a casing of a solid propellant engine, a tensioned and guided belt comprising a layer of adhesive material and a protective strip is fed from a deposit head, supported by a robot and comprising an unwinding device for unwinding the belt, a winding device for winding the strip, a first pressing roller for pressing the strip and the layer of adhesive material and rotatable about an axis thereof orthogonal to the feed path of the belt and a second pressing roller for pressing the adhesive material and the strip, rotatable about an axis thereof forming an angle other than 90° to the feed path and movable in opposite directions in a direction transversal to feed path.

Abstract: A polymeric formulation comprising at least one first epoxy resin having a density between 100 and 10,000 Pa·s, a blocked isocyanate, a polymer comprising hydroxy functional groups, a thermoplastic resin and a cross-linking agent, the polymer comprising hydroxyl functional groups with a hydroxyl content in the range 0.65 to 0.95 meq/g, the isocyanate-equivalents-to-polymer-OH-equivalents rate being in the range 0.60 to 1.1. The first epoxy resin is substantially semisolid at room temperature, the formulation comprising at least one second epoxy resin substantially liquid at room temperature, the first and second epoxy resins being present in a weight ratio from 60:40 to 80:20. These formulations are advantageously used for manufacturing prepregs and articles of composite material according to a dry winding process. By virtue of improved stability, a higher glass transition temperature, and a rheological profile result which can be chemically tailored to the needs of the impregnation/dry winding process.

Abstract: An aircraft power generating assembly having a mechanical gear transmission, and an electric machine integrated in the mechanical transmission; the electric machine having a stator connected directly to a fixed frame of the mechanical transmission, and a rotor surrounding and rotated by a rotary shaft of the mechanical transmission; and the opposite ends of the rotary shaft being connected to respective further rotary input/output shafts.

Abstract: In a turbine for aeronautic engines, a first and at least a second turbine disk rotating around a common axis respectively carrying a first and a second moving-blade crown, with which first and, respectively, second axial passages are defined through which a cooling air mass for the turbine disks can pass, a device for conveying cooling air being interposed between the first and the second axial passages to receive the mass of air passing through the first axial passages and send it through the second axial passages.

Abstract: A bladed rotor of a gas turbine for aeronautic engines is cooled by making an air mass flow through a plurality of passages, each one defined by a turbine disk on one side and by a root of a corresponding blade coupled to this turbine disk on the other, the incoming air of each passage being subdivided into two or more airflows and each flow being directed towards the turbine disk in a predefined direction.

Abstract: A rotor for turbomachines having a plurality of blades, and a damping member housed inside a chamber respectively arranged between each pair of adjacent blades of the rotor. The damping member is pushed, in use, by the centrifugal force against two surfaces, each of which is carried by a respective blade, which limit the respective chamber in a radially outward direction. The damping member is cup-shaped and provided with a base wall facing the two surfaces of the chamber and has three support bosses provided on one surface so that at least one of the three will contact one of the two surfaces and at least one other will contact the other of the two surfaces.

Abstract: A fuel mixture is fed to a gas turbine combustor by an injection assembly, which has an outer body with combustion-supporting air inlets; a conical tubular portion housed inside the outer body and partly defining an inner conduit and an outer annular conduit; and a first and second feed circuit for feeding liquid fuel to the inner conduit and outer annular conduit respectively; the first circuit having a ring of conduits with respective axes parallel to a generating line of an outer surface of the conical tubular portion.

Abstract: A rotor for turbomachines with shrouded blades comprising a row of a plurality of blades covered by an external ring, coaxial to said row of blades; the external ring being composed of a plurality of sectors, commonly referred to as shrouds, which are adjacent to one another and transversely and circumferentially attached to the end of respective blades; a damping member being arranged so as to straddle a respective pair of adjacent sectors and being pushed, in use, against radially internal surfaces of the sectors of the pair of adjacent sectors.

Abstract: In an epicyclic gear system, each planet gear is connected by a respective connecting pin to an asymmetric planet carrier having two plate portions connected to each other, and only one of which is connectable to a reaction member; and at least one end portion of each connecting pin and the plate portion connected to the reaction member are connected by a radially undulated annular wall flexible angularly and radially.

Abstract: Epicyclical gearing comprising a first and a second gear wheel turning around respective mutually parallel axes, each one comprising a respective first and a respective second crown wheel that are adjacent to each other; the gearing also comprising at least one third and at least one fourth gear wheel that are separate and mutually independent, a support body for the third and fourth gear wheels, the support body having hinge pins formed therewith as a one piece structure, the hinge pins providing a mount for the third and fourth gear wheels on the support body in a rotational manner around a third and, respectively, a fourth hinge axis parallel to the axes, the third gear wheel meshing with the respective first crown wheels and the respective fourth gear wheel meshing with the respective second crown wheels.

Abstract: An electromagnetic device has a stator and a rotor rotating between facing surfaces of the stator and bearing a plurality of magnets distributed at regular intervals along its periphery. The magnets are so arranged that they form a sequence of alternately opposite poles on the surfaces of the rotor directed towards the stator, and the stator comprises two sets of independently supported magnetic yokes located at both sides of the rotor in front of the magnets. The magnetic yokes have two axially oriented arms, the end surfaces of which, in static conditions of the rotor, at least partly face a pair of successive magnets on a same surface of the rotor.

Abstract: A process for manufacturing a component with a base of Co—Cr—Mo alloys having values of average ultimate elongation at 800° C. greater than 10% and of average yielding load at 800° C. greater than 400 MPa, comprising: obtaining a sintered component by additive sintering of powders of Co—Cr—Mo alloys containing carbides irregularly dispersed in the molten matrix; Conducting a first heat treatment on the sintered component for solubilization of the carbides at a temperature of between 1100° C. and 1300° C. for at least 2 hours to form a solubilization intermediate; and cooling the solubilization intermediate at a cooling rate at least equal to that of cooling in air to form a cooled intermediate; and conducting a second heat treatment on the cooled intermediate at a temperature of between 700° C. and 1000° C.

Abstract: In an epicyclic gear system, each planet gear is connected by a respective connecting pin to an asymmetric planet carrier having two plate portions connected to each other, and only one of which is connectable to a reaction member; and at least one end portion of each connecting pin and the plate portion connected to the reaction member are connected by a radially undulated annular wall flexible angularly and radially.

Abstract: A casing of a solid-propellant engine comprising a core and a layer of elastomeric material, set as coating for at least part of the core to provide a thermal protection of the core itself is obtained by: inserting the core in a forming mold so as to make within the mold two annular chambers separated from one another by the core; forming a strand of elastomeric material; obtaining a defined portion of elastomeric material by cutting the strand transversely to size in an external environment; and injecting the cut portion of elastomeric material simultaneously within both of the annular chambers.

Abstract: An aircraft power generating assembly having a mechanical gear transmission, and an electric machine integrated in the mechanical transmission; the electric machine having a stator connected directly to a fixed frame of the mechanical transmission, and a rotor surrounding and rotated by a rotary shaft of the mechanical transmission; and the opposite ends of the rotary shaft being connected to respective further rotary input/output shafts.