FIELD: the invention refers to flying vehicles with characteristics of an airplane and a helicopter.
SUBSTANCE: the flying vehicle is fulfilled in accord with the scheme of a biplane with lower lifting-carrying plane in a helicopter regime. The plane has half-planes with built-in turbofans with a regulated thrust vector with a gas drive from turbojet engines in quality of gas-generators. The vertical takeoff and landing aircraft is fulfilled in three variants with rotary, immovable and suspended lower lifting-carrying planes. The first variant has two lifting-carrying half-planes provided with rotary mechanisms. The second variant of the biplane scheme is remained as in helicopter so as in airplane regimes but in a rapid horizontal flight the inlet and outlet openings of the turbofans are closed with telescopic flap-fairings. The third variant has lifting-carrying half-planes suspended to the upper plane on consoles in the shape of lifting platforms with built-in turbofans. At that the lifting platforms are provided with a turning mechanism at certain angle around the longitudinal axle relatively to the flying vehicle. For creation of longitudinal thrust the turbofans are provided with a rotary mechanism around the transversal axle relatively to the flying vehicle. For increasing functional reliability of the lower lifting-carrying half-planes the driving pipelines from turbojet engines-gas-generators are combined in a single gas-feeding system. In the first and the third variants the length of gas-feeding pipelines is determined primary in accord with height of the consoles. The mechanism of controlling the vertical takeoff and landing aircraft in vertical regime has a mounted in tail turbojet engine in quality of a gas-generator and connected with it rudder nozzles with possibility of controlling the flying vehicle in vertical and horizontal planes of the flight on the basis of the single gas-streaming system.
EFFECT: creation of a flying vehicle with possibility of vertical takeoff and landing, vertical maneuvers and rapid horizontal flight.
17 cl, 7 dwg
