RU2000114837A - SYSTEM FOR TRANSFORMING A SELF-SUPPORTED HORIZONTAL FLIGHT PLANE AND A HORIZONTAL TAKE-OFF IN A HYBRID COMBINED SELF-SUPPORTED HORIZONTAL FLIGHT AROUND - Google Patents

Claims (6)

1. A system for converting a conventional self-sustaining horizontal take-off and landing aircraft into a hybrid self-sustaining horizontal flight with vertical take-off and landing, comprising, in addition to the power plant already existing in it, a hydraulic power plant that drives at least a blade rotor (1) intended for use during vertical take-off and landing and connected to the main engines of the aircraft (3), characterized in that the aircraft contains an additional engine (2) installed in its tail and / or lower part, wherein said at least additional engine (2) is configured to gradually tilt and rotate between two extreme positions, vertical and horizontal, these conventional engine means (3) of an airplane disconnected during vertical take-off and landing and in transition, and turned on during self-supported horizontal flight, and at least one rotor blade rotor (1) and at least one additional the engine (2) is turned on during vertical take-off and landing and in transition, and turned off during self-sustaining horizontal flight.  2. The system according to claim 1, characterized in that, depending on the size of the aircraft, at least one rotor blade rotor (1) is mounted on it, driven by a hydraulic propulsion system driven by main engines (3) mounted on the fuselage (4) the aircraft, in the nose, center, tail, or wings (5) to provide vertical take-off and landing of the aircraft.  3. The system according to one of the preceding paragraphs, characterized in that the aforementioned at least one additional engine (2) is at least a jet, at least a rocket or at least a turbofan engine, with or without hydraulic drive.  4. The system according to one of the preceding paragraphs, characterized in that the vertical rotor or screws (1) the vertical rotor or screws are fixed or fixed in place or in their places, even when they are turned off during horizontal flight, and it is possible that they appropriately hidden by fairings inside aerodynamic structures or inside wings (5).  5. The system according to one of the preceding paragraphs, characterized in that when the blade rotors (1) are not used, they are folded and placed in a casing in the fuselage of the aircraft.  6. The system according to one of the preceding paragraphs, characterized in that the aforementioned method is also used to convert helicopters into airplanes that combine the qualities of GDP and SOEs, to convert ships into water-air vehicles with GDP, or to convert cars into funds ground-to-air movements with GDP.