Abstract: An optical system for image projection, particularly for projection devices of the “head-mounted” type, includes a display, an optical system for focusing an image formed by the display, and a light guide having an extended body, with two opposite, longitudinal, plane and parallel faces, and opposite ends which define first reflecting surface for coupling into the light guide and second reflecting surface for extracting the image from the light guide. Each light ray which propagates through the light guide undergoes at least three internal total reflections on the parallel plane faces of the light guide. At least a surface of the focusing optical system is a portion of a surface free of rotational symmetry axes. Moreover, the two reflecting surfaces of the light guide are portions of surfaces free of rotational symmetry axes. Finally, the inlet pupil of the light guide coincides with the outlet pupil of the focusing system.

Abstract: An optical module for projecting a light beam comprises a solid body of transparent material into which a light source is sunk and which is delimited by an annular surface and by a central surface, and a substantially annular reflecting surface arranged around the solid body. The central and annular surfaces are suitable for receiving respective distinct portions of the luminous flux produced by the source. The reflecting surface may have a reflecting coating or may form part of a transparent body, in which case it works by total internal reflection. The reflecting surface reflects a portion of luminous flux refracted by the annular surface and shapes the flux into a predetermined distribution of luminous intensity about the principal axis. The annular surface is designed in a manner such as to reduce the overall thickness of the module by moving the refracted ray away from the principal axis.

Abstract: The lighting device comprises a light source and an associated hollow reflector of transparent material having an internal surface and an external surface which are close to and far away from the source respectively. The inner surface of the reflector has in cross section at least one transverse plane passing through the source a discontinuous profile forming a plurality of adjacent steps each of which has a first face through which rays originating from the source can pass and a second face essentially parallel to the rays originating from the source. The outer surface of the reflector has a profile comprising one or more arcs of curves.

Abstract: The aircraft comprises a fuselage, a main wing substantially of disc-like shape positioned above the fuselage, and a secondary wing which intersects the fuselage and is provided with movable control parts. The aircraft further comprises a main propulsion system including an internal combustion engine intended to drive a propeller positioned at the rear of the fuselage and a secondary propulsion system for the propulsion of the aircraft in a direction perpendicular to the ground. The secondary propulsion system includes a matrix of nozzles positioned on the lower surface of the secondary wing and arranged to emit the exhaust gases coming from the main engine in the form of micro-jets.

Abstract: Described herein is a transparent-display device for motor vehicles, to be used for presentation of information to the driver and/or to the passengers, said device comprising a plurality of LED sources, addressable individually or in groups through a series of conductive paths, deposited on a transparent underlayer and connected to a control electronics, in which: i) said LED sources are integrated in the form of dice, i.e., of elements obtained by dividing up a semiconductor wafer and without package; ii) said dice are integrated on, and electrically connected to, said underlayer via technologies of the chip-on-board type; and iii) said transparent underlayer 1 is pre-arranged for being at least in part superimposed on the windscreen of the vehicle, in such a way that at least part of the information presented to the user is superimposed on the background, said background being visible to the user through said windscreen.

Abstract: A method of fabrication of transparent LED devices, of the type comprising the operations of: i) providing a series of conductive paths on a transparent underlayer; ii) connecting said conductive paths to electronic control means; iii) associating to said underlayer an array of LED sources addressable individually or in groups through said conductive paths, in which i) said LED sources are integrated in the form of chips, i.e., of elements obtained by dividing up a semiconductor wafer and without package, via technologies of the chip-on-board type; ii) said method envisages the use of the flip-chip technique for die bonding, i.e., the electrical connection of the chip to the underlayer.

Abstract: Described herein is a transparent device for display of information superimposed on a background, said device comprising a plurality of LED sources, addressable individually or in groups through a series of conductive paths deposited on a transparent underlayer and connected to a control electronics, in which: i) said LED sources are integrated in the form of dice, i.e., of elements obtained by dividing up a semiconductor wafer and without package; and ii) at least one of said conductive paths is with interrupted stretches and replaced by stretches of metal wire, bonded to said paths through a wire-bonding operation.

Abstract: The invention describes a microaircraft, which can be associated for instance to a cellular phone, provided with at least four microrotors actuated with compressed fluid or by ring-shaped electric motors.

Abstract: A system for the production of electrical energy, comprising: a combustion chamber (14) made of material that is able to withstand high temperatures, an injection device (16) connected to said combustion chamber (14) by means of an injection conduit (15), means (17) for supplying combustion support substance into the combustion chamber (14) and means (18) for the removal of gaseous combustion products, means (26) for the selective emission of radiation onto the outer surface of the combustion chamber (14). The combustion chamber (14) is enclosed in a conversion chamber (20) within which are maintained sub-atmospheric pressure conditions, so that a substantial part of the heat developed by the combustion reaction is converted into electromagnetic radiation.

Abstract: VTOL micro-aircraft comprising a first and a second ducted rotor mutually aligned and distanced according to a common axis and whose propellers are driven in rotation in mutually opposite directions. Between the two ducted rotors are positioned a fuselage and a wing system formed by wing profiles forming an X or an H configuration and provided with control flaps.

Abstract: A module for projecting a light beam comprises a light source and a substantially flat support surface on which the source is arranged in a manner such as to emit light from only one side of the surface, and a reflector for reflecting the light emitted by the source. The reflector comprises a curved reflecting surface which extends on one side of the support surface, has a concavity facing towards the support surface, and can reflect the light coming from the source in a principal direction substantially parallel to the support surface of the source. An optical device for a module according to the invention and a vehicle front light assembly comprising a plurality of modules according to the invention form further subjects of the invention.

Abstract: A light-emitting device comprises a light source in the form of an incandescent filament, a substantial part of which is integrated in a host element having at least one portion structured according to nanometric dimensions. The nano-structured portion is in the form of a photonic crystal or of a Bragg grating, for the purpose of obtaining an amplified or increased emission of radiation in the region of the visible.

Abstract: A light concentrator is described, for a device for the conversion of solar radiation into electrical, thermal or chemical energy, capable of conveying the radiation towards a surface of the conversion device. The concentrator comprises at least one portion of Fresnel lens of rotational symmetry, one face of which has a plurality of crests disposed concentrically about a centre so as to form a segmented transverse profile of the portion of Fresnel lens. The profile is formed in such a manner that the focal distance of the Fresnel lens is variable in dependence on the radial distance from the centre of the lens. The variation of the focal distance is determined such that, when the Fresnel lens is illuminated by polychromatic radiation, the superposition of the distributions of irradiance, produced by the lens at the individual wavelengths constituting the spectrum of the incident radiation, generates a substantially uniform distribution of polychromatic irradiance on the conversion device.

Abstract: The flying machine includes a supporting structure including a central rotational support having a vertical axis connected to an essentially horizontal, preferably annular, peripheral support part, coaxial with the central support, at least one upper rotor including a central hub rotatable about the axis of the central support of the supporting structure, an outer channel-section ring supported by the peripheral part of the supporting structure by contactless suspension means, preferably magnetic suspension means, and a plurality of blades which extend from the hub to the channel-section ring and which are inclined with respect to the horizontal plane; and motor devices carried at least partially by the peripheral part of the supporting structure and operable to cause rotation of the rotor with respect to this structure in a predetermined direction.

Abstract: The lighting device comprises a light source and an associated hollow reflector of transparent material having an internal surface and an external surface which are close to and far away from the source respectively. The inner surface of the reflector has in cross section at least one transverse plane passing through the source a discontinuous profile forming a plurality of adjacent steps each of which has a first face through which rays originating from the source can pass and a second face essentially parallel to the rays originating from the source. The outer surface of the reflector has a profile comprising one or more arcs of curves.

Abstract: VTOL aircraft comprising a first and a second ducted rotor positioned at the ends of a vertical fuselage and whose propellers are driven to rotate in mutually opposite directions. Control flaps for orientation and transverse flight are operatively associated at least to the lower ducted rotor.

Abstract: A three-dimensional structure in the form of filament (6) for an incandescent lamp comprises a plurality of tungsten microfilaments (6A) having micrometric and/or nanometric dimensions, to form a photonic crystal structure. The microfilaments (6A) are arranged so as to form a series of microcavities in the three-dimensional structure (6), a means having a refraction index different from that of tungsten being present within said microcavities. The described arrangement makes it possible to prevent propagation and spontaneous emission of IR radiation of specific wavelenghts e allows at the same time propagation and spontaneous emission of visible radiation.

Abstract: A light source composed of a planar, or substantially level, flat or curved, rigid or flexible, matrix of microfilaments integrated on a single substrate and capable of emitting light by incandescence when supplied by an electric current.

Abstract: A lighting device, comprising a luminous source consisting of a LED (5) that is placed between the flanges (2,3) of a primary reflector (1), which is essentially V-shaped. A secondary reflector (7), composed of an elongated element with steps (8), runs along the extension of one of the flanges (3) of the primary reflector (1), while an elongated transparent diffuser (9) runs along the extension of the other flange (2).

Abstract: VTOL micro-aircraft comprising a first and a second ducted rotor mutually aligned and distanced according to a common axis and whose propellers are driven in rotation in mutually opposite directions. Between the two ducted rotors are positioned a fuselage and a wing system formed by wing profiles forming an X or an H configuration and provided with control flaps.