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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. Th

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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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 defin

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. 2. The PAC defined in claim 1, wherein two or more thrusters are arranged on each opposite side of said fuselage.3. The PAC defined in claim 2, wherein at least three thrusters are arranged on each opposite side.4. The PAC defined in claim 1, wherein two or more thrusters are arranged on each opposite side along a straight line.5. The PAC defined in claim 1, wherein the thrust of each of said thrusters is independently controllable.6. The PAC defined in claim 1, wherein at least one of said thrusters on each side may be controlled to adjust the direction of thrust.7. The PAC defined in claim 6, wherein an outlet of said at least one thruster is a tube for directing the flow of air, and wherein said direction of thrust is controlled by moving said tube.8. The PAC defined in claim 6, wherein said at least one thruster has a rotatable impeller defining an impeller axis, and wherein said direction of thrust is controlled by tilting said impeller axis.9. The PAC defined in claim 1, further comprising an additional independently powered thruster attached to said fuselage at one of said front side and said rear side thereof for directing thrust in at least one of a forward and rearward direction of the craft.10. The PAC defined in claim 1, wherein said thrusters are disposed in said wing between said leading edge and said trailing edge.11. The PAC defined in claim 1, wherein said wing is at least one of foldable and extendable toward and away from said fuselage, thereby to respectively reduce its length for storage and increase its length for operation.12. The PAC defined in claim 1, wherein each of said ducted fan units includes a duct having an inlet and an outlet and an impeller for driving air through said duct from said inlet to said outlet.13. The PAC defined in claim 12, wherein each of said ducted fan units further includes a prime mover for rotating said impeller.14. The PAC defined in claim 1, wherein at least one of the thrusters on each opposite side of the compartment comprises ducted fan apparatus including:(1) a cylindrical first tube having an inlet, an outlet and a linear, first central axis which is disposed at an angle to the vertical when said craft is oriented in its normal upright position such that the inlet is located forward of the outlet, in relation to the direction of travel of said aircraft; (2) a first impeller disposed in said first tube and arranged to rotate about said first central axis to generate airflow from the inlet to the outlet; (3) a first prime mover coupled to drive said first impeller; and (4) a second tube having an inlet and an outlet, the outlet of said second tube having substantially the same internal cross-sectional diameter area as that of said first tube, the outlet of said second tube extending into the inlet of said first tube, the inlet of said second tube facing forward in relation to said direction of travel and having.a substantially horizontal, second central axis. 15. The PAC defined in claim 14, wherein said first prime mover is disposed in said first tube adjacent to said first impeller.16. The PAC defined in claim 15, wherein said first prime mover is mounted on a plurality of stator blades which constrain air to flow through said first tube in the direction of said first central axis.17. The PAC defined in claim 15, wherein said first prime mover is an internal combustion engine.18. The PAC defined in claim 17, wherein the internal combustion engine has an intake port for the intake of air, said intake port being disposed outside of said first tube.19. The PAC defined in claim 14, wherein said ducted fan apparatus further comprises a third tube having an inlet and an outlet, the inlet of said third tube being substantially cylindrical and having substantially the same internal diameter as that of said first tube, the outlet of said first tube extending into the inlet of said third tube.20. The PAC defined in claim 19, wherein the outlet of said third tube has a circular cross section.21. The PAC defined in claim 19, wherein the outlet of said third tube has a third central axis, and wherein said apparatus further includes means for adjusting the orientation of said third central axis with respect to that of said first central axis, thereby adjusting the direction of outflow of air.22. The PAC defined in claim 21, wherein said third tube has at least one of a flexible and an articulated portion arranged between the inlet and outlet thereof to allow for the adjustment of orientation of said third central axis.23. The PAC defined in claim 14, further comprising a second impeller disposed in said first tube and arranged to rotate about said first central axis in a direction opposite to the direction of rotation of said first impeller, said second impeller serving to redirect the air to flow in the axial direction within said first tube and to increase the speed of air at the outlet of said first tube.24. The PAC defined in claim 23, wherein said first prime mover drives both said first and said second impeller.25. The PAC defined in claim 23, further comprising a second prime mover coupled to drive said second impeller.26. The PAC defined in claim 25, wherein said second prime mover is disposed in said first tube adjacent to said second impeller.27. The PAC defined in claim 26, wherein said second prime mover is coupled to said first prime mover to rotate in synchronism in opposite direction.28. The PAC defined in claim 26, wherein the second prime mover is a second internal combustion engine having an intake port for the intake of air, said intake port being disposed outside of said first tube.29. The PAC defined in claim 14, wherein the inlet of said second tube has a circular opening.30. The PAC defined in claim 14, wherein the inlet of said second tube has a substantially rectangular opening, said opening having upper and lower substantially horizontal edges and two side edges.31. The PAC defined in claim 30, wherein the upper edge of the opening in the inlet of said second tube has an aerodynamic contour which produces lift due to airflow into such inlet.32. The PAC defined in claim 30, wherein the lower edge of the opening in the inlet of said second tube has an aerodynamic contour which produces lift due to airflow into such inlet.33. The PAC defined in claim 14, wherein the inlet of said second tube has at least one edge surrounding an inlet opening, said edge defining a substantially planar face of the inlet which forms an acute angle with respect to said second central axis.34. The PAC defined in claim 33, wherein said acute angle is in the range of 35 to 55 degrees.35. The PAC defined in claim 34, wherein said acute angle is substantially 45 degrees.36. The PAC defined in claim 14, further comprising second ducted fan apparatus, substantially identical to said apparatus defined in claim 15, disposed adjacent to said apparatus defined in claim 15, with the inlets of the second tubes thereof disposed one above the other.37. The PAC defined in claim 14, further comprising second ducted fan apparatus, substantially identical to said apparatus defined in claim 15, disposed adjacent to said apparatus defined in claim 15, with the inlets of the second tubes thereof disposed laterally adjacent each other.38. The PAC defined in claim 14, wherein said first axis is disposed at an angle to the vertical in the range of 15 to 35 degrees.39. The PAC defined in claim 1, wherein said passenger compartment is configured as a lifting body, to provide lift to the craft during forward motion through the air.40. The PAC defined in claim 1, wherein said passenger compartment has a top and a center of gravity, said PAC further comprising a parachute arranged at the top, in substantially vertical alignment with the center of gravity, for deployment in the event of thruster failure.41. The PAC defined in claim 1, wherein said passenger compartment has a bottom and a center of gravity, said PAC further comprising an airbag arranged at on the bottom, in substantially vertical alignment with the center of gravity, for deployment in the event of thruster failure.42. A vertical take-off and landing aircraft comprising, in combination:(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, and wherein 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. 43. The aircraft defined in claim 42, comprising at least four thrusters arranged in said wing, with two thrusters arranged on each side of said fuselage.44. The aircraft defined in claim 42, comprising at least six thrusters arranged in said wing, with three thrusters arranged on each side of said fuselage.45. The aircraft defined in claim 42, comprising at least eight thrusters arranged in said wing, with four thrusters arranged on each side of said fuselage.46. The aircraft defined in claim 42, wherein said thrusters are arranged along at least one straight line which extends from one end of said wing to the other.47. The aircraft defined in claim 46, wherein said thrusters are arranged along at least two straight lines which extend from one end of said wing to the other.48. The aircraft defined in claim 47, wherein said two lines are parallel.49. The aircraft defined in claim 42, wherein the lift to drag ratio is in the range of 4:1 to 10:1.50. 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. 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.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, andwherein 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. 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, andwherein 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. 54. The aircraft defined in claim 53, wherein said angle of said impeller axis with respect to the vertical is adjustable, to adjust the direction of thrust of said ducted fan unit, between zero degrees and an angle greater than zero degrees.55. The aircraft defined in claim 1, wherein the ducted fan units are equal to or less than about 5 feet in diameter.56. The aircraft defined in claim 55, wherein the ducted fan units have a diameter in the range of 2 to 5 feet.57. In a personal aircraft (PAC) capable of vertical take-off and landing (VTOL) and comprising, in combination:(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, and wherein 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. 58. The PAC defined in claim 57, wherein said ducted fan has a substantially vertical tube with an upper end and a lower end, wherein an impeller is arranged in said tube to move and accelerate air from said upper end to said lower end to provide direct lift to the aircraft, and wherein said tube has a tapered lip at said upper end to provide induced lift to the aircraft.59. The aircraft defined in claim 57, wherein said at least one ducted fan is equal to or less than about 5 feet in diameter.60. The aircraft defined in claim 42, wherein each impeller is equal to or less than about 5 feet in diameter.61. The aircraft defined in claim 59, wherein impeller has a diameter in the range of 2 to 5 feet.62. The aircraft defined in claim 1, wherein the lift to drag ratio is in the range of 4:1 to 10:1.