Abstract: An electro-optical system capable of being embarked aboard mobile ground or flying units, to determine the optical flow generated by obstacles in relative motion with respect to the mobile unit. The system comprises radiation emitter means (5), receiver means (1) for converting the radiation reflected by the objects into electrical signals and means (8) for processing the signals generated by the receiver means. The receiver means (1) are based on vision sensors with matrix configuration. The emitter means (5, 6) shape the radiation beam in such a way that the radiation reflected by the objects and collected by the receiver means impacts at least on a part of the receiver matrix. The processing means compute the optical flow only on the elements of the receiver matrix that are impacted by the radiation.

Abstract: An electro-optical system capable of being embarked aboard mobile ground or flying units, to determine the optical flow generated by obstacles in relative motion with respect to the mobile unit. The system comprises radiation emitter means (5), receiver means (1) for converting the radiation reflected by the objects into electrical signals and means (8) for processing the signals generated by the receiver means. The receiver means (1) are based on vision sensors with matrix configuration. The emitter means (5, 6) shape the radiation beam in such a way that the radiation reflected by the objects and collected by the receiver means impacts at least on a part of the receiver matrix. The processing means compute the optical flow only on the elements of the receiver matrix that are impacted by the radiation.

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: 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: The system allows the generation and distribution of energy on board a motor vehicle provided with a propulsion unit, a tank for fuel at least one distribution network or line for electric energy, electrical energy generation devices connected to the said at least one distribution network or line, and a plurality of selectively activatable electrical utiliser devices or apparatus connected or connectable to the said at least one distribution network or line. The said electrical energy generator devices comprise (at least) a microcombustor electricity generator matrix or battery connected to the fuel tank, and a supervision and control unit associated with this generator matrix or battery and coupled to the distribution network or line and arranged to control the operation of the said generator matrix or battery in a predetermined manner as a function of the electrical power required or consumed by the said network or line.

Abstract: Bidimensional or three-dimensional, single-layer or multilayer nanostructure, whose electric conductivity B in the total structure has a highly non-linear behavior due to local tunnel effect between adjacent clusters, and it can be varied at will by varying the voltage applied to the electrodes.

Abstract: The combustor comprises a stationary structure and at least one tubular rotor supported rotatably about an axis by the structure by means of contactless suspension devices there being formed within this rotor at least one combustion chamber having at least one orientated lateral outflow aperture for the ejection of the combustion gases. The rotor has a narrow circumferential slot through which there extend at least one controlled stationary injector of fuel and combustion agent and an associated igniter which is also stationary. A control unit operates the injector and the igniter according to predetermined procedures, in such a way as to generate a detonation wave which is propagated in the chamber, and to cause the rotor to rotate as a result of the thrust due to the combustion gases emitted through the lateral outflow aperture.

Abstract: Interface system for assisting an operator during a work stage comprising a support structure wearable by the operator, with a transparent screen placed in front of the operator's eyes to permit him to see a portion of a background; a virtual image generator for producing an optical signal directed towards the operator's retina so as to form a virtual image at a predetermined distance from the operator's eyes and superimposed on the background; a recording device integral with the operator's head, to record part of the operator's visual field and make available a signal representative of the visual field; a processing device for processing the signal from the recording device and generating a visual information signal of use to the operator for carrying out the work stage; and a device of reception/transmission for sending the signal from the recording device to the processing device, and rendering the information signal to the virtual image generator.

Abstract: The device includes a combustor comprising an inlet chamber or region intended to receive a flow of fuel and a combustion supporter at high pressure, an outlet chamber or region or combustion product exhaust at relatively lower pressure, and at least one separation element of nano-porous or micro-porous semi-conductor material which separates the inlet chamber or region from the outlet chamber or region. The separation element has a plurality of nano-pores or micro-pores passing therethrough which define communication passages between the inlet clad chamber or region and the outlet chamber or region. The surface of these pores is at least partly clad in a layer of an electrically conductive or semi-conductive material which, relative to the semi-conductor material of the separation element forms an essentially extended junction, in particular a p-n junction or a Schottky junction or a hetero junction.

Abstract: A light-emitting device comprises a structure defining an orderly and periodic series of cavities of nanometric dimensions, in which a process of catalytic combustion is confined. The dimensions and/or the distance between the micro-cavities are selected to obtain a light emission in the visible and prevent and/or attenuate at the same time emission of infrared radiation.

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: 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: 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: 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.