Patent ID: 11472545

Abstract:
The present invention relates to the propulsion system and aircraft with vertical take-off and landing—VTOL that uses aerodynamic phenomena of thrust amplification, including at zero speed, to reduce the thrust/weight ratio.According to the invention, an individual aircraft 1, with vertical take-off and landing, uses a fuselage 2 in the form of a frame 3 that merges two propulsion system, 4 and 5 one in the front and the other in the rear, of the bi-planar type, located at the ends of the fuselage 2. The propulsion system 4 uses two wings 6 and 7, which are superimposed, parallel and distanced by a certain distance D. The rear wing 7 is fixed perpendicularly to the frame 3 in its median area, so that an angle α between 25° and 80° is formed with the horizontal plane in static position. The front wing 6 and the rear wing 7 are secured at their ends by two jet limiters 8. Similarly the rear propulsion system 5 uses two wings 8 and 10. On each rear wing 7 and 10 are installed a number of electric motors 11, preferably located at equal distances from each other. Each electric motor 11 actuates a tractor propeller 12.