Abstract

The invention refers to a VTOL aircraft of the type that uses certain aerodynamic phenomena to increase the lifting force and to reduce the thrust/weight ratio. An aircraft 1 uses a propulsion system 2 consisting of four thrust producing elements, two in front 3 and two in rear 4. Each front thrust producing element 3 contains at least one front rotor 5 operated by at least one front electric motor, fixed on a fuselage 10. Each rear thrust producing element 4 contains at least one rear rotor 7 driven by at least a rear electric motor 8, fixed on the fuselage 10. On the fuselage 10 is attached symmetrically a front wing 12. On the fuselage 10 is attached symmetrically a rear wing 13. The wing 12 and 13 are used also in static conditions respectively in take-off and landing.

IPC Classes  ?

• B64U 10/20 - Vertical take-off and landing [VTOL] aircraft
• A61G 1/06 - Supports for stretchers, e.g. to be placed in or on vehicles
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64C 39/04 - Aircraft not otherwise provided for having multiple fuselages or tail booms
• B64C 39/08 - Aircraft not otherwise provided for having multiple wings
• B64U 50/19 - Propulsion using electrically powered motors
• B64U 60/10 - Undercarriages specially adapted for use on water
• B64U 101/58 - UAVs specially adapted for particular uses or applications for life-saving or rescue operationsUAVs specially adapted for particular uses or applications for medical use for medical evacuation, i.e. the transportation of persons or animals to a place where they can receive medical care
• B64U 101/60 - UAVs specially adapted for particular uses or applications for transporting passengersUAVs specially adapted for particular uses or applications for transporting goods other than weapons

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.

IPC Classes  ?

• B64C 39/08 - Aircraft not otherwise provided for having multiple wings
• B64C 39/06 - Aircraft not otherwise provided for having disc- or ring-shaped wings
• B64C 29/00 - Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
• B64C 27/26 - Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
• B64C 27/08 - Helicopters with two or more rotors