Abstract: An aircraft is described comprising: a support element; a shaft rotating about an axis; a pair of oblique rolling bearings mounted so as to couple the shaft to the support element rotatingly about the axis; the rolling bearings comprising: respective first races cooperating radially in contact with a first component defined by one from the support element and the shaft; respective second races cooperating radially in contact with a second component defined by the other from the support element and the shaft; and respective pluralities of rolling elements adapted to roll on the first and second races; the aircraft further comprises a pair of preloaded elastic members, which couple the first races to the first component respectively, axially and in an elastically yielding manner.

Abstract: A heat exchanger for a transmission unit of an aircraft is described that comprises: a first module defining a first feed path for a first fluid to be cooled; a second module defining a second feed path for a second cooling fluid; the first and second feed paths being thermally coupled to each other; each second module comprising: at least one cell formed by an inlet for a second cooling fluid; an outlet for the second cooling fluid, which is arrange on the opposite side to the inlet along a first direction; a first wall thermally coupled to the first path; a pair of second walls; and a plurality of fins projecting in a cantilever fashion from the first wall. The heat exchanger further comprises at least a first row of fins, which lie on a plane orthogonal to the first direction, the fins of the first row extending at progressively increasing distances from one of the second walls along a second direction orthogonal to the first direction.

Abstract: A rotor for an aircraft is described, comprising an input shaft rotatable around a first axis; an output member rotatable around a second axis; a coupling element functionally interposed between the input shaft and the output member and adapted to transmit the motion from the input shaft to the output member; the coupling element is configured to allow, in use, a fixed or variable inclination between the respective first and second axes; the coupling element comprises at least a first corrugated element made of an elastically deformable material; the first corrugated element allows the inclination through elastic deformation.

Abstract: An anti-torque rotor is described comprising: a mast rotatable about a first axis; a plurality of blades rotatable about respective second axes; an element slidable along the first axis with respect to the mast, rotating integrally with the mast and operatively connected to the blades; a control rod slidable along axis; a first bearing with a first ring rotating integrally with element, a second ring radially internal to the first ring with respect to the first axis and a plurality of first rolling bodies; a third ring sliding integrally with the control rod along the first axis and angularly fixed with respect to the first axis; and a locking element arranged in a standard configuration, in which it prevents the relative rotation of the second and third rings and movable from the standard configuration to at least one emergency configuration, in which it renders the second ring free to rotate with respect to the third ring, when the first bearing is in a failure condition.

Abstract: An aircraft is described comprising: a support element; a shaft rotating about an axis; a pair of oblique rolling bearings mounted so as to couple the shaft to the support element (rotatingly about the axis; the rolling bearings comprising: respective first races cooperating radially in contact with a first component (defined by one from the support element and the shaft; respective second races cooperating radially in contact with a second component (defined by the other from the support element and the shaft; and respective pluralities of rolling elements adapted to roll on the first and second races; the aircraft further comprises a pair of preloaded elastic members, which couple the first races to the first component respectively, axially and in an elastically yielding manner.

Abstract: A heat exchanger for a transmission unit of an aircraft is described that comprises: a first module defining a first feed path for a first fluid to be cooled; a second module defining a second feed path for a second cooling fluid; the first and second feed paths being thermally coupled to each other; each second module comprising: at least one cell formed by an inlet for a second cooling fluid; an outlet for the second cooling fluid, which is arrange on the opposite side to the inlet along a first direction; a first wall thermally coupled to the first path; a pair of second walls; and a plurality of fins projecting in a cantilever fashion from the first wall. The heat exchanger further comprises at least a first row of fins, which lie on a plane orthogonal to the first direction, the fins of the first row extending at progressively increasing distances from one of the second walls along a second direction orthogonal to the first direction.

Abstract: A helicopter collapsible deck having at least one longitudinal member and at least one cross member, which extend respectively in a first and second direction intersecting at a point; the cross member is interrupted at the point of intersection; the deck also has an anchoring device for connecting the longitudinal member and the cross member at the point of intersection; and the anchoring device has at least one local permanent deformation section lying in a plane crosswise to the deck and for dissipating the energy transmitted to the deck in the event of impact.

Abstract: A helicopter collapsible deck having at least one longitudinal member and at least one cross member, which extend respectively in a first and second direction intersecting at a point; the cross member is interrupted at the point of intersection; the deck also has an anchoring device for connecting the longitudinal member and the cross member at the point of intersection; and the anchoring device has at least one local permanent deformation section lying in a plane crosswise to the deck and for dissipating the energy transmitted to the deck in the event of impact.

Abstract: A fuel manifold for the direct injection of fuel into an internal combustion engine comprising a head provided with a number of cylinders, a number of injectors, each of which is connected to the fuel manifold and is adapted directly to inject the fuel into a respective cylinder, and an intake manifold, which is connected to the head in order to supply fresh air to the cylinders, the fuel manifold being formed by a single monolithic body which is made from thixotropic aluminum by means of a pressure die casting process and comprises a supply duct adapted to distribute the fuel to the injectors, and a flange disposed laterally to the supply duct, the flange being adapted to be secured by a plurality of screws to the head of the engine and comprising a number of coupling members each of which is adapted to bring a respective cylinder into communication with the intake manifold.

Abstract: A fuel manifold for the direct injection of fuel into an internal combustion engine comprising a head provided with a number of cylinders, a number of injectors, each of which is connected to the fuel manifold and is adapted directly to inject the fuel into a respective cylinder, and an intake manifold, which is connected to the head in order to supply fresh air to the cylinders, the fuel manifold being formed by a single monolithic body which is made from thixotropic aluminum by means of a pressure die casting process and comprises a supply duct adapted to distribute the fuel to the injectors, and a flange disposed laterally to the supply duct, the flange being adapted to be secured by a plurality of screws to the head of the engine and comprising a number of coupling members each of which is adapted to bring a respective cylinder into communication with the intake manifold.

Abstract: Method for producing salt grains in which the salt is dissolved in a liquid solvent inside a mixing tank so as to form a saline solution which is supersaturated with salt and which is then atomized inside a drying tower where a stream of hot air circulates; the atomizing process being designed to produce a plurality of drops of saline solution, all of approximately the same size, and the stream of hot air being designed to evaporate the liquid solvent contained in each drop so as to cause the salt present in the said drop to solidify into a salt grain of essentially spherical shape; given that the dimensions of the salt grains depend on the dimensions of the drops of saline solution, it is possible to obtain salt grains of the desired size by producing drops of saline solution of a suitable size during the atomizing process.

Abstract: A method including a preheating stage wherein rheocast light alloy ingots are preheated to a temperature within the solidification range of the alloy; and a die casting stage wherein a mold is filled with the semiliquid alloy. The preheating stage is performed in a forced-convection-heated tunnel furnace, with the ingots housed inside cup-shaped containers which, following a temperature check, are tipped by a robot to unload the ingots into the injection chamber of a die casting machine. Work is conducted within a temperature range depending on the composition of the alloy, and such that, at the minimum permissible injection temperature, the ingot is incapable of maintaining its own shape, and, at the maximum permissible injection temperature, the apparent viscosity of the ingot is such as to ensure the mold is filled under laminar flow conditions.