VTOL personal aircraft

• US 20030062443A1
• Filed: 04/02/2002
• Published: 04/03/2003
• Est. Priority Date: 10/02/2001
• Status: Abandoned Application

• Current Assignee: Karl F. Milde Jr
• Original Assignee: Karl F. Milde Jr
• Inventors: Milde, Karl F. Jr., Wagner, Joseph, Pruszenski, Anthony Jr.
• Application Number:
  US10/114,754
• Publication Number:
  US 20030062443A1
• Time in Patent Office: Days
• US Class Current: 244/12.3
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

A personal aircraft (PAC) capable of vertical take-off and landing (VTOL) comprises a passenger compartment having a front, a rear and two sides, and a plurality of independently powered thrusters attached to the outer periphery of the compartment. At least two thrusters are disposed on each side of the compartment. The thrusters, which are preferably ducted fan units, are capable of providing a vertically upward force to the compartment. The thrusters preferably comprise a “Levitator” which creates lift from the airfoil-like air inlet as well as from the acceleration of air from inlet to outlet.

Claims

1. 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) a plurality of independently powered thrusters attached to said compartment, with at least two thrusters disposed on each of two opposite sides of said compartment, said thrusters being capable of providing vertical lift to said compartment;

wherein there is a total of at least four thrusters for redundancy in operation.

2. The PAC defined in claim 1, wherein said two or more thrusters on each opposite side are arranged adjacent each other in a cluster.

3. The PAC defined in claim 2, wherein four thrusters are arranged in said cluster on each opposite side.

4. The PAC defined in claim 1, wherein said two or more thrusters on each side are arranged along a straight line.

5. The PAC defined in claim 1, wherein said two or more thrusters on each side are arranged along a curved line.

6. The PAC defined in claim 1, wherein the thrust of each of said thrusters is independently controllable from said compartment.

7. The PAC defined in claim 1, wherein the outlet of at least one of said two or more thrusters on each side may be controlled to adjust the direction of thrust.

8. The PAC defined in claim 7, wherein the 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.

9. The PAC defined in claim 1, further comprising an additional independently powered thruster attached to said compartment 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, further comprising at least one wing on each side of said compartment to provide lift during forward movement of the craft.

11. The PAC defined in claim 10, wherein said wing on each side of the compartment is foldable toward and away from said compartment.

12. The PAC defined in claim 10, wherein said wing on each side of the compartment is collapsible and extendable, respectively, toward and away from said compartment.

13. The PAC defined in claim 1, wherein at least one of the thrusters on each opposite side of the compartment includes a duct having an inlet and an outlet and means for driving air through said duct from said inlet to said outlet.

14. The PAC defined in claim 13, wherein said air driving means includes an impeller, disposed for rotation within said duct, and a prime mover for rotating said impeller.

15. 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.

16. The PAC defined in claim 15, wherein said first prime mover is disposed in said first tube adjacent to said first impeller.

17. The PAC defined in claim 16, 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.

18. The PAC defined in claim 16, wherein said first prime mover is an internal combustion engine.

19. The PAC defined in claim 18, wherein the internal combustion engine has an intake port for the intake of air, said intake port being disposed outside of said first tube.

20. The PAC defined in claim 15, 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.

21. The PAC defined in claim 20, wherein the outlet of said third tube has a circular cross section.

22. The PAC defined in claim 20, 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.

23. The PAC defined in claim 22, 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.

24. The PAC defined in claim 15, 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.

25. The PAC defined in claim 24, wherein said first prime mover drives both said first and said second impeller.

26. The PAC defined in claim 24, further comprising a second prime mover coupled to drive said second impeller.

27. The PAC defined in claim 26, wherein said second prime mover is disposed in said first tube adjacent to said second impeller.

28. The PAC defined in claim 27, wherein said second prime mover is coupled to said first prime mover to rotate in synchronism in opposite direction.

29. The PAC defined in claim 27, wherein said second prime mover is a second internal combustion engine.

30. The PAC defined in claim 29, wherein the second internal combustion engine has an intake port for the intake of air, said intake port being disposed outside of said first tube.

31. The PAC defined in claim 15, wherein the inlet of said second tube has a circular opening.

32. The PAC defined in claim 15, 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.

33. The PAC defined in claim 32, 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.

34. The PAC defined in claim 32, 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.

35. The PAC defined in claim 15, 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.

36. The PAC defined in claim 35, wherein said acute angle is in the range of 35 to 55 degrees.

37. The PAC defined in claim 36, wherein said acute angle is substantially 45 degrees.

38. The PAC defined in claim 15, 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.

39. The PAC defined in claim 15, 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.

40. The PAC defined in claim 15, wherein said first axis is disposed at an angle to the vertical in the range of 15 to 35 degrees.

65. 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.

66. 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.

67. 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.

41. Ducted fan apparatus arranged on a vertical take-off and landing (VTOL) aircraft, said apparatus comprising, in combination:

(a) 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 aircraft 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;

(b) 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;

(c) a first prime mover coupled to drive said first impeller; and

(d) a second tube having an inlet and an outlet, the outlet of said second tube having the same internal cross-sectional area as that of said first tube, the outlet of said second tube extending coaxially with, and smoothly 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.

42. The ducted fan apparatus defined in claim 41, wherein said first prime mover is disposed in said first tube adjacent to said first impeller.

43. The ducted fan apparatus defined in claim 42, wherein said first prime mover is an internal combustion engine.

44. The ducted fan apparatus defined in claim 42, 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.

45. The ducted fan apparatus defined in claim 41, further comprising a third tube having an inlet and an outlet, the inlet of said third tube being cylindrical and having the same internal diameter as that of said first tube, the outlet of said first tube extending coaxially with, and smoothly into, the inlet of said third tube.

46. The ducted fan apparatus defined in claim 45, wherein the outlet of said third tube has a circular cross section.

47. The ducted fan apparatus defined in claim 45, 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.

48. The ducted fan apparatus defined in claim 47, 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.

49. The ducted fan apparatus defined in claim 41, 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 increase the outflow of air at the outlet of said first tube.

50. The ducted fan apparatus defined in claim 49, wherein said first prime mover drives both said first and said second impeller.

51. The ducted fan apparatus defined in claim 49, further comprising a second prime mover coupled to drive said second impeller.

52. The ducted fan apparatus defined in claim 51, wherein said second prime mover is disposed in said first tube adjacent to said second impeller.

53. The ducted fan apparatus defined in claim 41, wherein the inlet of said second tube has a circular cross section.

54. The ducted fan apparatus defined in claim 41, 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.

55. The ducted fan apparatus defined in claim 54, 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.

56. The ducted fan apparatus defined in claim 54, 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.

57. The ducted fan apparatus defined in claim 41, 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.

58. The ducted fan apparatus defined in claim 57, wherein said acute angle in the range of 35 to 55 degrees.

59. The ducted fan apparatus defined in claim 58, wherein said acute angle is substantially 45 degrees.

60. The ducted fan apparatus defined in claim 43, wherein the internal combustion engine has an intake port for the intake of air, said intake port being disposed outside of said first tube.

61. The ducted fan apparatus defined in claim 41, further comprising second ducted fan apparatus, substantially identical to said apparatus defined in claim 41, disposed adjacent to said apparatus defined in claim 41, with the inlets of the second tubes thereof disposed one above the other.

62. The ducted fan apparatus defined in claim 41, further comprising second ducted fan apparatus, substantially identical to said apparatus defined in claim 41, disposed adjacent to said apparatus defined in claim 41, with the inlets of the second tubes thereof disposed laterally adjacent each other.

63. The ducted fan apparatus defined in claim 41, wherein said first axis is disposed at an angle to the vertical in the range of 15 to 35 degrees.

64. The ducted fan apparatus defined in claim 63, wherein said first axis is disposed at an angle to the vertical of substantially 26 degrees.