VTOL personal aircraft
First Claim
1. A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) and having a center of gravity, said aircraft comprising, in combination:
- (a) a fuselage forming a passenger compartment and having a four sides, including a front side, a rear side and two lateral sides, said fuselage defining a central longitudinal axis of said aircraft;
(b) fixed wing having a leading edge and a trailing edge, said wing being attached to the fuselage and extending outward with respect to said two lateral sides at a longitudinal position along said central axis of said aircraft such that the center of gravity of said aircraft is between said leading edge and said trailing edge;
(c) a plurality of thrusters, each comprising a thruster outlet duct and being attached to said wing, said thrusters being capable of providing both vertical lift and horizontal thrust to said aircraft, said thrusters being movable, between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust;
wherein the lift-to-drag ratio of the aircraft resulting from forward motion of the craft through the air and excluding vertical lift provided by said thrusters is greater than 4;
1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH.
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Accused Products
Abstract
A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a fixed wing and a fuselage with a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters, preferably integrated into the wing, on each side of the fuselage. The aircraft has a lift to drag ratio equal to or greater than 2. The thrusters, which are ducted fan units capable of providing a vertically upward force to the aircraft, are provided with such redundancy that the aircraft can hover with at one thruster inoperative on each side of the fuselage. At least one thruster on each side of the fuselage preferably comprises a “levitator” which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.
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Citations
62 Claims
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1. A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) and having a center of gravity, said aircraft comprising, in combination:
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(a) a fuselage forming a passenger compartment and having a four sides, including a front side, a rear side and two lateral sides, said fuselage defining a central longitudinal axis of said aircraft;
(b) fixed wing having a leading edge and a trailing edge, said wing being attached to the fuselage and extending outward with respect to said two lateral sides at a longitudinal position along said central axis of said aircraft such that the center of gravity of said aircraft is between said leading edge and said trailing edge;
(c) a plurality of thrusters, each comprising a thruster outlet duct and being attached to said wing, said thrusters being capable of providing both vertical lift and horizontal thrust to said aircraft, said thrusters being movable, between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust;
wherein the lift-to-drag ratio of the aircraft resulting from forward motion of the craft through the air and excluding vertical lift provided by said thrusters is greater than 4;
1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25, 26, 27, 28, 29, 30, 31, 32, 33, 34, 35, 36, 37, 38, 39, 40, 41, 55, 56, 62)
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42. A vertical take-off and landing aircraft comprising, in combination:
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(a) a horizontal fixed wing having two ends and an upper wing surface and a lower wing surface;
(b) a fuselage disposed on said wing substantially midway between said two ends; and
(c) an even number of thrusters, each arranged in and integrated into said wing, with the same number of thrusters on each side of said fuselage, to direct air from said upper surface to said lower surface of said wing, each thruster including;
(1) an inlet at or above said upper surface;
(2) an outlet at or below said lower surface;
(3) a circular air duct disposed between said inlet and said outlet;
(4) an impeller disposed in said air duct for directing and accelerating air from said inlet to said outlet; and
(5) a prime mover connected to drive said impeller;
wherein the lift-to-drag ratio of the aircraft resulting from forward motion of the craft through the air and excluding vertical lift provided by said thrusters is greater than 4;
1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH, andwherein said thrusters, including the prime movers thereof, are movable between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust. - View Dependent Claims (43, 44, 45, 46, 47, 48, 49, 60)
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50. In an aircraft comprising a fuselage with a longitudinal fuselage axis and an elongate fixed wing having a longitudinal wing axis extending transversely to said fuselage axis, an upper surface, a lower surface and a cross-sectional profile, transverse to said wing axis, forming a wing airfoil, the improvement comprising a plurality of ducted fan units arranged in said wing, each ducted fan unit having a impeller, rotatable about an impeller axis, and a circular duct arranged concentrically with said impeller axis and surrounding said impeller, said circular duct having an outlet opening with a central axis, and means for varying the direction of said impeller axis to vary the direction of thrust of said ducted fan unit, whereby the pitch of the aircraft may be controlled by varying the direction of thrust of said ducted fan units,
wherein the lift-to-drag ratio of the aircraft resulting from forward motion of the craft through the air and excluding vertical lift provided by said ducted fan units is greater than 4: - 1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH, and
wherein said thrusters, including the impeller axis thereof, are movable between a first position in which the provide vertical lift and a second position in which they provide horizontal thrust.
- 1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH, and
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51. In an aircraft comprising a fuselage with a central longitudinal axis and an elongate fixed wing having a longitudinal wing axis extending transversely to said central axis, an upper surface, a lower surface and a cross-sectional profile, transverse to said wing axis, forming a wing airfoil, the improvement comprising a plurality of ducted fan units arranged in said wing, each ducted fan unit having a impeller, rotatable about an impeller axis, and a circular duct arranged concentrically with said impeller axis and surrounding said impeller, at least some of said ducted fan units having means for controlling the angle of the impeller axes thereof with respect to the vertical, whereby components of thrust may be imparted to said aircraft in the vertical direction and in a direction transverse to the vertical, and wherein the lift-to-drag ratio of the aircraft resulting from forward motion of the craft through the air and excluding vertical lift provided by said ducted fan units is greater than 4:
- 1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH.
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52. In an aircraft comprising (a) a fuselage with a central, longitudinal, fuselage axis extending through a center of gravity of the aircraft, and (b) an elongate fixed wing having a longitudinal wing axis extending transversely to the direction of said fuselage axis and extending in the direction of said fuselage axis, from a leading edge to a trailing edge, both in front of and behind said center of gravity, said wing having an upper surface, a lower surface and a cross-sectional profile, transverse to said wing axis, forming a wing airfoil, the improvement comprising a plurality of ducted fan units arranged in said wing, each ducted fan unit having a impeller, rotatable about an impeller axis, and a circular duct arranged concentrically with said impeller axis and surrounding said impeller, said circular duct having an inlet opening surfaces which extend smoothly into said upper surface of said wing, wherein the lift-to-drag ratio of the aircraft resulting from forward motion of the craft through the air and excluding vertical lift provided by said ducted fan units is greater than 4:
- 1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH, and
wherein said ducted fan units, including the impeller axes thereof, are movable between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust.
- 1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH, and
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53. In an aircraft comprising a fuselage with a central longitudinal axis and an elongate fixed wing having a longitudinal wing axis extending transversely to said central axis, an upper surface, a lower surface and a cross-sectional profile, transverse to said wing axis, forming a wing airfoil, the improvement comprising a plurality of ducted fan units arranged in said wing, each ducted fan unit having a impeller, rotatable about an impeller axis, and a circular duct arranged concentrically with said impeller axis and surrounding said impeller, at least some of said ducted fan units having an impeller axis disposed at an angle with respect to the vertical, whereby components of thrust may be imparted to said aircraft in the vertical direction and in a direction transverse to the vertical, wherein the lift-to-drag ratio of the aircraft resulting from forward motion of the craft through the air and excluding vertical lift provided by said ducted fan units is greater than 4:
- 1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH, and
wherein said ducted fan units, including the impeller axes thereof, are movable between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust. - View Dependent Claims (54)
- 1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH, and
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57. In a personal aircraft (PAC) capable of vertical take-off and landing (VTOL) and comprising, in combination:
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(a) a passenger compartment having a four sides, including a front side, a rear side and two lateral sides;
(b) at least two thrusters arranged to vertically lift and to provide horizontal thrust to said aircraft, each of said thrusters having an air impeller arranged to rotate about an impeller axis; and
(c) at least one substantially horizontal wing, attached to said compartment and extending outward from said two lateral sides, said wing having a wingspan from one end thereof to the other;
the improvement wherein said wing is extendible from a first position with a first wingspan to a second position with a second wingspan which is greater than said first wingspan, wherein the lift-to-drag ratio of the aircraft resulting from forward motion of the craft through the air and excluding vertical lift provided by said at least one ducted fan unit is greater than 4;
1 with the aircraft flying at a cruising speed in the range of 50 to 100 MPH, andwherein said thrusters, including the impeller axes thereof, are movable between a first position in which they provide vertical lift and a second position in which they provide horizontal thrust, whereby the wingspan, and therefore the transverse area occupied by said aircraft is variable. - View Dependent Claims (58, 59, 61)
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Specification