Aerodynamically stable, VTOL aircraft
First Claim
1. An aerodynamically stable, vertical take-off and landing (VTOL) aircraft comprising:
- (a) a main fuselage body symmetrically balanced about a centerline axis in a main horizontal direction and adapted for VTOL flight while oriented substantially in a horizontal plane with respect to the ground;
(b) an air-impeller-rotor engine mounted in a forward position of said main fuselage body in symmetric relation to said centerline axis, said air-impeller-rotor engine being oriented substantially along a vertical axis normal to the horizontal plane and having dual impeller rotors which are mounted within a vertically-oriented air channel duct to impel air thrust in a substantially vertically downward direction for supplying vertical lift to the aircraft, and which are driven to rotate in opposite rotational directions so as to balance engine torque forces;
(c) at least one air-impeller-rotor engine mounted in a rearward position of said main fuselage body arranged in symmetric relation to said centerline axis and provided so as to balance engine torque forces, said at least one air-impeller-rotor engine being oriented substantially along a vertical axis normal to the horizontal plane and having a rotor which is mounted within a vertically-oriented air channel duct to impel air thrust in a substantially vertically downward direction for supplying vertical lift to the aircraft, and(d) said at least one rearward air-impeller-rotor engine having an air directing assembly for directing at least a part of the impeller thrust flow of air from the engine in a desired angular direction with respect to the horizontal plane to generate a horizontal thrust component for maneuvering or translation movement of the aircraft,wherein said air directing assembly is an air vane assembly mounted below said air impeller engine having one or more rotatable vanes in a parallel array mounted to a rotatable support ring, a first actuator means for rotating the vanes at a selected deflection angle on an axis in the horizontal plane, and a second actuator means for rotating the support ring on the vertical axis, for directing the thrust flow of air in a desired angular direction.
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Accused Products
Abstract
A hover aircraft employs an air impeller engine having an air channel duct and a rotor with outer ends of its blades fixed to an annular impeller disk that is driven by magnetic induction elements arrayed in the air channel duct. The air-impeller engine is arranged vertically in the aircraft frame to provide vertical thrust for vertical takeoff and landing. Preferably, the air-impeller engine employs dual, coaxial, contra-rotating rotors for increased thrust and gyroscopic stability. An air vane assembly directs a portion of the air thrust output at a desired angle to provide a horizontal thrust component for flight maneuvering or translation movement. The aircraft can employ a single engine in an annular fuselage, two engines on a longitudinal fuselage chassis, three engines in a triangular arrangement for forward flight stability, or other multiple engine arrangements in a symmetric, balanced configuration. Other flight control mechanisms may be employed, including side winglets, an overhead wing, and/or air rudders or flaps. An integrated flight control system can be used to operate the various flight control mechanisms. Electric power is supplied to the magnetic induction drives by high-capacity lightweight batteries or fuel cells. The hover aircraft is especially well suited for applications requiring VTOL deployment, hover operation for quiet surveillance, maneuvering in close air spaces, and long duration flights for continuous surveillance of ground targets and important facilities requiring constant monitoring.
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Citations
17 Claims
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1. An aerodynamically stable, vertical take-off and landing (VTOL) aircraft comprising:
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(a) a main fuselage body symmetrically balanced about a centerline axis in a main horizontal direction and adapted for VTOL flight while oriented substantially in a horizontal plane with respect to the ground; (b) an air-impeller-rotor engine mounted in a forward position of said main fuselage body in symmetric relation to said centerline axis, said air-impeller-rotor engine being oriented substantially along a vertical axis normal to the horizontal plane and having dual impeller rotors which are mounted within a vertically-oriented air channel duct to impel air thrust in a substantially vertically downward direction for supplying vertical lift to the aircraft, and which are driven to rotate in opposite rotational directions so as to balance engine torque forces; (c) at least one air-impeller-rotor engine mounted in a rearward position of said main fuselage body arranged in symmetric relation to said centerline axis and provided so as to balance engine torque forces, said at least one air-impeller-rotor engine being oriented substantially along a vertical axis normal to the horizontal plane and having a rotor which is mounted within a vertically-oriented air channel duct to impel air thrust in a substantially vertically downward direction for supplying vertical lift to the aircraft, and (d) said at least one rearward air-impeller-rotor engine having an air directing assembly for directing at least a part of the impeller thrust flow of air from the engine in a desired angular direction with respect to the horizontal plane to generate a horizontal thrust component for maneuvering or translation movement of the aircraft, wherein said air directing assembly is an air vane assembly mounted below said air impeller engine having one or more rotatable vanes in a parallel array mounted to a rotatable support ring, a first actuator means for rotating the vanes at a selected deflection angle on an axis in the horizontal plane, and a second actuator means for rotating the support ring on the vertical axis, for directing the thrust flow of air in a desired angular direction. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12)
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13. An aerodynamically stable, vertical take-off and landing (VTOL) aircraft comprising:
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(a) a main fuselage body symmetrically balanced about a centerline axis in a main horizontal direction and adapted for VTOL flight while oriented substantially in a horizontal plane with respect to the ground; (b) an air-impeller-rotor engine mounted in a forward position of said main fuselage body in symmetric relation to said centerline axis, said air-impeller-rotor engine being oriented substantially along a vertical axis normal to the horizontal plane and having dual impeller rotors which are mounted within a vertically-oriented air channel duct to impel air thrust in a substantially vertically downward direction for supplying vertical lift to the aircraft, and which are driven to rotate in opposite rotational directions so as to balance engine torque forces; (c) at least one air-impeller-rotor engine mounted in a rearward position of said main fuselage body arranged in symmetric relation to said centerline axis and provided so as to balance engine torque forces, said at least one air-impeller-rotor engine being oriented substantially along a vertical axis normal to the horizontal plane and having a rotor which is mounted within a vertically-oriented air channel duct to impel air thrust in a substantially vertically downward direction for supplying vertical lift to the aircraft, and (d) said at least one rearward air-impeller-rotor engine having an air directing assembly for directing at least a part of the impeller thrust flow of air from the engine in a desired angular direction with respect to the horizontal plane to generate a horizontal thrust component for maneuvering or translation movement of the aircraft, wherein said impeller rotor is formed with impeller blades having inner ends fixed to a central hub and outer ends fixed to an annular impeller disk rotatable about a rotational axis substantially aligned with the vertical axis to propel a downward vertical flow of air to provide vertical lift to the aircraft, and a magnetic induction drive for driving the impeller rotor substantially friction-free within the air channel duct. - View Dependent Claims (14, 15, 16, 17)
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Specification