An STOL or VTOL winged aircraft comprises a fuselage and a fixed wing attached to the fuselage and extending outward from the two lateral sides thereof, forming one wing component extending outward from one side of the fuselage and a second wing component extending outward from the opposite side of
An STOL or VTOL winged aircraft comprises a fuselage and a fixed wing attached to the fuselage and extending outward from the two lateral sides thereof, forming one wing component extending outward from one side of the fuselage and a second wing component extending outward from the opposite side of the fuselage. At least one "thruster" is disposed in each wing component to provide vertical lift to the aircraft when the aircraft is stationary or moving forward only slowly. The thruster includes a shaft mounted for rotation in the respective wing component and extending substantially parallel to the wing axis and a plurality of fan blades attached to the shaft for movement of air. A shroud is preferably arranged in each wing component, adjacent to the fan blades, for directing the airflow downward or rearward.
대표청구항▼
What is claimed is: 1. A personal aircraft (PAC) capable of short take-off and landing (STOL) or vertical take-off and landing (VTOL) and having a center of gravity, said aircraft comprising, in combination: (a) an elongate fuselage having two lateral sides and forming a passenger compartment, said
What is claimed is: 1. A personal aircraft (PAC) capable of short take-off and landing (STOL) or vertical take-off and landing (VTOL) and having a center of gravity, said aircraft comprising, in combination: (a) an elongate fuselage having two lateral sides and forming a passenger compartment, said fuselage being arranged along a longitudinal axis of said aircraft; (b) an elongate fixed wing attached to the fuselage for providing vertical lift to the aircraft upon forward motion thereof through the air, said fixed wing having a leading edge, a trailing edge and a longitudinal wing axis between them, said fixed wing extending outward from the two lateral sides of the fuselage with the wing axis substantially perpendicular to said longitudinal axis of the aircraft, the center of gravity of said aircraft being located in a region between the leading edge and the trailing edge of said wing, said wing having a first wing component extending outward from one lateral side of said fuselage and second wing component extending outward from an opposite lateral side of said fuselage; and (c) at least one thruster disposed in each wing component, substantially midway between said leading edge and said trailing edge thereof, for providing additional vertical lift to said aircraft whether or not said aircraft is in motion, said thruster comprising: (1) at least one shaft mounted for rotation in the respective wing component and extending substantially parallel to said wing axis; and (2) a plurality of fan blades attached to each shaft for movement of air upon rotation of the respective shaft, each fan blade having an outer extremity; and (d) a prime mover coupled to rotate said at least one shaft in each wing component in such direction that the outer extremities of the fan blades move rearward, toward the trailing edge of the respective wing component, when above the shaft, and move forward, toward the leading edge of the wing component, when below the shaft, thereby causing air to move in a rearward direction above the shaft. 2. The aircraft defined in claim 1, wherein the fan blades are elongate and extend substantially parallel to the shaft to which they are attached. 3. The aircraft defined in claim 1, further comprising a shroud in each wing component, adjacent said fan blades, which directs the air downward, thereby providing vertical lift to said aircraft when said aircraft is in the STOL and VTOL mode. 4. The aircraft defined in claim 3, wherein at least a portion of said shroud is movable, thereby to control the amount of air that is directed downward. 5. The aircraft defined in claim 1, wherein each thruster comprises two shafts mounted for rotation in each wing component, said two shafts being substantially parallel to said wing axis and to each other, each of said two shafts being driven by a common prime mover and having a plurality of fan blades for movement of air. 6. The aircraft defined in claim 5, wherein said two shafts mounted in each wing component are driven in counter rotation by said prime mover. 7. The aircraft defined in claim 6, wherein said two shafts are mounted sufficiently close together such that their respective fan blades are interleaved. 8. The aircraft defined in claim 7, wherein the fan blades are configured to inhibit air from passing between said two shafts, thereby forming a Roots-type blower configuration. 9. The aircraft defined in claim 6, wherein said two shafts are mounted sufficiently far apart such that their respective fan blades are not interleaved. 10. The aircraft defined in claim 9, wherein said two shafts are driven in counter rotation by said prime mover in a direction causing air to be directed downward between said two shafts. 11. The aircraft defined in claim 5, wherein said two shafts mounted in each wing component are driven in the same direction of rotation by said prime mover. 12. The aircraft defined in claim 1, each wing component has an upper wing surface and a lower wing surface, and wherein said at least one shaft is mounted between said upper and lower wing surface of the respective wing component in which it is mounted. 13. The aircraft defined in claim 12, wherein said at least one shaft is mounted closer to said upper wing surface than to said lower wing surface. 14. The aircraft defined in claim 13, wherein said fan blades extend upward beyond said upper wing surface of the respective wing component. 15. The aircraft defined in claim 12, wherein said at least one shaft is moveable in the vertical direction between a first position, in which its associated fan blades protrude upward from the upper surface of its associate wing component, and a second position in which its fan blades are substantially contained between the upper surface and the lower surface of said wing component. 16. The aircraft defined in claim 1, wherein the fan blades extend outward substantially radially from the respective shaft to which they are attached. 17. The aircraft defined in claim 1, wherein each fan blade includes a radial portion which extends outward substantially radially with respect to said shaft and a tip portion which extends in a substantially circumferential direction about said shaft. 18. The aircraft defined in claim 17, wherein said tip is moveable in the circumferential direction with respect to the fan blade to which it is attached. 19. The aircraft defined in claim 1, further comprising a prime mover disposed in the fuselage for rotating both of said shafts simultaneously. 20. The aircraft defined in claim 1, further comprising a substantially vertical fin disposed at the free end of each wing component.
Dekel, Guy; Zivan, Lior; Efraty, Yoav; Wolff, Amit; Volovick, Avner, System, a method and a computer program product for maneuvering of an air vehicle.
Dekel, Guy; Zivan, Lior; Efraty, Yoav; Wolff, Amit; Volovick, Avner, System, a method and a computer program product for maneuvering of an air vehicle with tiltable propulsion unit.
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