Abstract: The unmanned aerial vehicle, UAV, has a fuselage (1) with at least one rotating shaft (2) and one wing (3) positioned on the rotating shaft (2), protruding from either side of the fuselage (1). Preferably, the UAV has at least one rotor propeller (4) arranged on each rotating shaft (2), on either side of the fuselage (1), with one or more rotor blades (4a) and a housing (4b), which includes an actuator. The UAV is capable of shifting between a first flight mode using rotatable wings that rotate freely around the rotating shaft (2) only due to a direction and strength of wind impinging against a surface of the wings (3) and a downstream flow generated by the rotor propellers (4), and a second flight mode using fixed wings, kept in a predetermined position by a wing-locking mechanism, preferably a substantially horizontal position.

Abstract: The platform comprises supporting legs (12) fastened to the platform (10), and a control unit (13) and provides an electrical charging system including a plurality of coplanar adjacent electroconductive plates (14), with adjacent edges electrically insulated, arranged on an electrically insulated support. Each electroconductive plate (14) is connected by an electroconductive cable (15) to the control unit (13) and to a power source (16), wherein the electroconductive plate (14), electroconductive cable (15) and control unit (13) form an electrical circuit and the control unit (13) is configured to detect a change of an electric potential and/or current of the electrical circuit due to a UAV, landing on said platform and providing at least two points of contact with two different electroconductive plates (14). The platform supply energy, from power source to said two different electroconductive plates (14) using corresponding electroconductive cables (15) in order to charge powering means of said UAV.

Abstract: The invention relates to an aerodyne with vertical take-off and landing ability and the ability to generate lift by means of both rotors and fixed wings, which includes: a fuselage (1); two fixed wings (2); two front rotors (11) and two rear rotors (12) arranged symmetrically and actuated by means of motors (13), each rotor (10) being attached to a central portion of a fixed wing (2) by means of a support (14) and connected pivotably about a connection shaft (E2), which allows changing the inclination of each rotor (10) from a longitudinal forward movement position, in which they propel the aerodyne horizontally, to a lift position in which it provides vertical lift; said rear rotors being in a lift position partially overlapping a portion of the wing including a flap (20) freely connected to the rest of the wing, the position thereof being determined between a lift position and a longitudinal forward movement position by the effect of the aerodynamic thrust.

Abstract: The unmanned aerial vehicle, UAV, has a fuselage (1) with at least one rotating shaft (2) and one wing (3) positioned on the rotating shaft (2), protruding from either side of the fuselage (1). Preferably, the UAV has at least one rotor propeller (4) arranged on each rotating shaft (2), on either side of the fuselage (1), with one or more rotor blades (4a) and a housing (4b), which includes an actuator. The UAV is capable of shifting between a first flight mode using rotatable wings that rotate freely around the rotating shaft (2) only due to a direction and strength of wind impinging against a surface of the wings (3) and a downstream flow generated by the rotor propellers (4), and a second flight mode using fixed wings, kept in a predetermined position by a wing-locking mechanism, preferably a substantially horizontal position.

Abstract: The invention relates to an aerodyne with vertical take-off and landing ability and the ability to generate lift by means of both rotors and fixed wings, which includes: a fuselage (1); two fixed wings (2); two front rotors (11) and two rear rotors (12) arranged symmetrically and actuated by means of motors (13), each rotor (10) being attached to a central portion of a fixed wing (2) by means of a support (14) and connected pivotably about a connection shaft (E2), which allows changing the inclination of each rotor (10) from a longitudinal forward movement position, in which they propel the aerodyne horizontally, to a lift position in which it provides vertical lift; said rear rotors being in a lift position partially overlapping a portion of the wing including a flap (20) freely connected to the rest of the wing, the position thereof being determined between a lift position and a longitudinal forward movement position by the effect of the aerodynamic thrust.

Abstract: A control system and method for a thermal circuit that includes a control unit (1) and a valvular device which regulate the passage of a heat transfer fluid (6) through the inside of a thermal circuit, and a thermoelectric element (3) powering the control unit (1) from the heat of the heat transfer fluid (6). The control unit (1) and/or the valvular device are configured to regulate the circulation of the heat transfer fluid (6) through the inside of the thermal circuit, in order to always maintain a sufficient minimum flow to assure, at all times, the electric power supply of the control unit (1). The method includes using a control system to carry out regulation of the circulation of the heat transfer fluid which assures the electric power supply of part or the entire control system.

Abstract: A control system and method for a thermal circuit that includes a control unit (1) and a valvular device which regulate the passage of a heat transfer fluid (6) through the inside of a thermal circuit, and a thermoelectric element (3) powering the control unit (1) from the heat of the heat transfer fluid (6). The control unit (1) and/or the valvular device are configured to regulate the circulation of the heat transfer fluid (6) through the inside of the thermal circuit, in order to always maintain a sufficient minimum flow to assure, at all times, the electric power supply of the control unit (1). The method includes using a control system to carry out regulation of the circulation of the heat transfer fluid which assures the electric power supply of part or the entire control system.

Abstract: Straight-line potentiometer including a casing with a longitudinal opening in which slides a carrier having an electroconductive slider which provides electrical contact between an electroconductive slideway and an electroresistive slideway. The slider is provided with a centrally disposed offset portion which is inserted between the lugs of the carrier. The slideways are arranged on opposite sides of the longitudinal opening and run parallel to the opening. The carrier is made up of an operating stem and two resilient lugs, arranged so as to form a fork, extending through the longitudinal opening. The ends of the lugs are further provided with toes which engage the inner edges of the longitudinal opening and allow the carrier and slider to smoothly slide along the opening. The improved straight-line potentiometer is also provided with a plurality of resilient grips situated on opposite ends of the longitudinal line of the carrier and engaging lateral sectors of the slider in a riding arrangement.