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 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.