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. Ducted fans a preferably arranged on both sides of the aircraft for providing additional vertical thrust.
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 having a leading edge and a trailing edge and a longitudinal wing axis between them, said fixed wing being attached to the fuselage and extending outward from the two lateral sides thereof with the wing axis substantially perpendicular to said longitudinal axis of said 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; (c) at least one shaft mounted for rotation in each respective wing component and extending substantially parallel to said wing axis; and (d) a plurality of fan blades attached to each shaft for movement of air upon rotation of the respective shaft, each fan blade having opposite first and second edges, each fan blade extending substantially radially outward from the shaft, to which its first edge is attached, to its opposite second edge. 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 to and above said fan blades, which extends substantially parallel to the upper surface of said wing and constricts air that is moved by said fan blades to flow in a direction substantially parallel to said upper surface of said wing, thereby to increase the speed of airflow over said upper surface and enhance the vertical lift of said aircraft wing. 4. The aircraft defined in claim 1, further comprising a prime mover disposed in the fuselage for rotating both of said shafts simultaneously. 5. The aircraft defined in claim 4, wherein said prime mover is a barrel-type internal combustion engine. 6. The aircraft defined in claim 1, further comprising a substantially vertical fin disposed at the free end of each wing component. 7. The aircraft defined in claim 1, further comprising at least one ducted fan disposed on each side of said longitudinal axis for providing substantially vertical thrust to said aircraft. 8. The aircraft defined in claim 7, wherein the ducted fans are selectively moveable between a first position in which they provide substantially vertical thrust and a second position in which they provide substantially horizontal thrust. 9. The aircraft defined in claim 7, wherein said ducted fans are mounted on both sides of said fuselage in front of said wing. 10. The aircraft defined in claim 7, wherein said ducted fans are mounted at the outer end of each wing component. 11. The aircraft defined in claim 7, wherein at least one of said ducted fans is mounted within each wing component. 12. The aircraft defined in claim 1, wherein said shafts and said fan blades are configured to move air in the direction toward the trailing edge of said wing. 13. 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 having a leading edge and a trailing edge and a longitudinal wing axis between them, said fixed wing being attached to the fuselage and extending outward from the two lateral sides thereof with the wing axis substantially perpendicular to said longitudinal axis of said 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; (c) at least one drive shaft mounted for rotation in each respective wing component and extending substantially parallel to said wing axis; (d) a plurality of fan blades attached to each shaft for movement of air upon rotation of the respective shaft, each fan blade having opposite first and second edges, each fan blade extending substantially radially outward from the shaft, to which its first edge is attached, to its opposite second edge; (e) at least one ducted fan disposed on each respective wing component for providing substantially vertical thrust to said aircraft, each ducted fan having a substantially vertical fan shaft with a plurality of fan blades attached thereto; (f) a gearbox for mechanically coupling said drive shaft with said fan shaft on each wing component; and (g) a prime mover disposed in said fuselage for rotating both of said drive shafts simultaneously.
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이 특허에 인용된 특허 (1)
Ducan Terry A. (13311 Old Oaks Fenton MI 48430), VTOL aircraft control method.
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