Vertical takeoff and landing aerial vehicle

• US 6,691,949 B2
• Filed: 07/08/2002
• Issued: 02/17/2004
• Est. Priority Date: 07/06/2001
• Status: Expired due to Term

• Current Assignee: Charles Stark Draper Laboratory Incorporated
• Original Assignee: Charles Stark Draper Laboratory Incorporated
• Inventors: Gupta, Neil R., Plump, John M.
• Primary Examiner(s): Swiatek, Robert P.
• Application Number:
  US10/191,733
• Publication Number:
  US 20030052222A1
• Time in Patent Office: 589 Days
• Field of Search: 244/7.B, 244/12.2, 244/12.3, 244/23.A, 244/23.C, 244/34.A
• US Class Current: 244/12.2
• CPC Class Codes: B64C 29/02 having its flight directional axis vertical when grounded
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 39/062 having annular wings
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/20 Vertical take-off and landing [VTOL] aircraft flying platforms B64U10/13; helicopters B64U10/17
• CPC Class Codes: B64U 2101/30 for imaging, photography or videography
• CPC Class Codes: B64U 2101/31 for surveillance
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/24 Coaxial rotors
• CPC Class Codes: B64U 30/26 Ducted or shrouded rotors
• CPC Class Codes: B64U 40/10 for adjusting control surfaces or rotors
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/14 ducted or shrouded
• CPC Class Codes: B64U 70/80 Vertical take-off or landing, e.g. using rockets rotorcrafts B64U10/10; VTOL aircraft B64U10/20

Abstract

An aerial vehicle including a toroidal fuselage having a longitudinal axis, and a duct extending along the longitudinal axis between a leading edge and a trailing edge of the fuselage, first and second counter-rotating, variable pitch rotor assemblies coaxially mounted within the duct of the fuselage, and at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage, wherein at least a portion of the canard wing comprises a control surface having a variable angle of attack. The invention provides an aerial vehicle that can take-off and land vertically, hover for extended periods of time over a fixed spatial point, and operate in confined areas. The aerial vehicle also has the ability to transition between a hover and high speed forward flight.

Claims

1. An aerial vehicle comprising:

a toroidal fuselage having a longitudinal axis, and a duct extending along the longitudinal axis between a leading edge and a trailing edge of the fuselage;

first and second counter-rotating, variable pitch rotor assemblies coaxially mounted within the duct of the fuselage; and

at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage, wherein at least a portion of the at least one canard wing comprises a control surface having a variable angle of attack, wherein the at least one canard wing includes a trailing edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage.

2. An aerial vehicle according to claim 1, wherein the entire at least one canard wing comprises a control surface.

3. An aerial vehicle according to claim 1, further comprising an actuator operatively connected to the at least one movable canard wing for varying the angle of attack.

4. An aerial vehicle according to claim 1, wherein the at least one canard wing comprises four canard wings radially extending from the longitudinal axis of the fuselage.

5. An aerial vehicle according to claim 1, further comprising a central pod extending beyond the leading edge of the fuselage coaxially along the longitudinal axis and outer pods extending from the leading edge of the fuselage parallel with the longitudinal axis, and wherein the at least one canard wing comprises four canard wings radially extending with respect to the longitudinal axis from the central pod to the outer pods.

6. An aerial vehicle according to claim 5, wherein the outer pods contain fuel cells.

7. An aerial vehicle according to claim 6, wherein the fuel cells comprise batteries.

8. An aerial vehicle according to claim 5, wherein the outer pods contain actuators operatively connected to the movable canard wing for varying the angles of attack of the wings.

9. An aerial vehicle according to claim 5, wherein distal ends of the outer pods comprise landing gear.

10. An aerial vehicle according to claim 5, wherein the central pod contains an avionics bay.

11. An aerial vehicle according to claim 5, wherein the central pod contains a payload bay.

12. An aerial vehicle according to claim 5, wherein the central pod contains an actuator operatively connected to the rotor assemblies for varying the pitch of the rotor assemblies.

13. An aerial vehicle according to claim 1, wherein the fuselage includes an internal toroidal fuel bladder positioned against the leading edge of the fuselage.

14. An aerial vehicle according to claim 1, further comprising at least one engine mounted within the fuselage, and a drive train operatively connecting the engine to the first and the second rotor assemblies.

15. An aerial vehicle according to claim 14, wherein the drive train includes a gearbox located between the rotor assemblies, a rotatable drive shaft operatively connected between the engine and the gearbox, and the rotor assemblies include rotatable propeller hubs operatively connected between the gearbox and propeller blades of the rotor assemblies.

16. An aerial vehicle according to claim 15, wherein the drive shaft and the propeller hubs are operatively connected to the gearbox through bevel gears.

17. An aerial vehicle according to claim 16, wherein the bevel gears operatively connecting the gear box comprise straight bevel gears.

18. An aerial vehicle according to claim 15, wherein the drive shaft includes substantially parallel primary and secondary drive shafts connected by a connecting drive shaft, wherein the primary drive shaft extends between the engine and the connecting drive shaft and the secondary drive shaft extends between the connecting drive shaft and the gear box.

19. An aerial vehicle according to claim 18, wherein the drive shafts are operatively connected through bevel gears.

20. An aerial vehicle according to claim 19, wherein the bevel gears operatively connecting the drive shafts comprise straight bevel gears.

21. An aerial vehicle according to claim 19, wherein the bevel gears operatively connecting the drive shafts comprise a gear reduction train.

22. An aerial vehicle according to claim 14, wherein the drive train includes a clutch.

23. An aerial vehicle according to claim 22, wherein the clutch comprises a Sprague clutch.

24. An aerial vehicle according to claim 14, wherein the drive train includes a flywheel.

25. An aerial vehicle according to claim 1, wherein the rotor assemblies are received on a single propeller shaft and each comprises:

a hub mounted on the propeller shaft for rotation about an axis of the propeller shaft; and

at least two propeller blades extending radially outwardly from the hub.

26. An aerial vehicle according to claim 25, wherein each propeller includes an axis extending substantially normal with respect to the axis of the propeller shaft, and the propeller blades are rotatable with respect to the propeller hub about the propeller axes.

27. An aerial vehicle according to claim 26, wherein each rotor assembly further comprises a coupling assembly received on the propeller shaft and movable with respect to the propeller shaft parallel with the axis of the propeller shaft, and linkages pivotally connected between the coupling assembly and the propeller blades.

28. An aerial vehicle according to claim 27, further comprising a movable rod connected to the coupling assemblies and a linear actuator connected to the actuation rod.

29. An aerial vehicle according to claim 28, wherein the propeller shaft is hollow and the rod is movably received within the propeller shaft.

30. An aerial vehicle comprising:

a toroidal fuselage having a longitudinal axis, and a duct extending along the longitudinal axis;

a hollow propeller shaft coaxially extending along the axis and within the duct;

first and second rotor assemblies coaxially mounted on the propeller shaft within the duct, wherein each rotor assembly includes,

a hub mounted on the propeller shaft for rotation about the axis,

at least two propeller blades extending radially outwardly from the hub, wherein each propeller includes an axis extending substantially normal with respect to the axis of the duct, and the propeller blades are rotatably about the propeller axes,

a coupling assembly received on the propeller shaft and movable with respect to the propeller shaft parallel with the axis of the fuselage,

linkages pivotally connected between the coupling assembly and the propeller blades so that movement of the coupling assembly on the propeller shaft causes rotation of the propeller blades about the propeller axes, and

a rod received within the hollow propeller shaft, movable with respect to the propeller shaft parallel with the axis of the duct, and connected to the coupling assemblies so that movement of the rod within the propeller shaft causes movement of the coupling assembly on the propeller shaft.

31. An aerial vehicle according to claim 30, further comprising a linear actuator connected to the rod.

32. An aerial vehicle according to claim 30, further comprising at least one engine mounted within the fuselage, and a drive train operatively connecting the engine to the first and the second rotor assemblies.

33. An aerial vehicle according to claim 32, wherein the drive train includes a gearbox located between the rotor assemblies, a rotatable drive shaft operatively connected between the engine and the gearbox, and the rotatable propeller hubs are operatively connected to the gearbox.

34. An aerial vehicle according to claim 33, wherein the drive shaft and the propeller hubs are operatively connected to the gearbox through bevel gears.

35. An aerial vehicle according to claim 34, wherein the bevel gears operatively connecting the gear box comprise straight bevel gears.

36. An aerial vehicle according to claim 33, wherein the drive shaft includes substantially parallel primary and secondary drive shafts connected by a connecting drive shaft, wherein the primary drive shaft extends between the engine and the connecting drive shaft and the secondary drive shaft extends between the connecting drive shaft and the gear box.

37. An aerial vehicle according to claim 36, wherein the drive shafts are operatively connected through bevel gears.

38. An aerial vehicle according to claim 37, wherein the bevel gears operatively connecting the drive shafts comprise straight bevel gears.

39. An aerial vehicle according to claim 37, wherein the bevel gears operatively connecting the drive shafts comprise a gear reduction train.

40. An aerial vehicle according to claim 32, wherein the drive train includes a clutch.

41. An aerial vehicle according to claim 40, wherein the clutch comprises a Sprague clutch.

42. An aerial vehicle according to claim 32, wherein the drive train includes a flywheel.

43. An aerial vehicle according to claim 30, further comprising at least one canard wing secured to the toroidal fuselage and having a leading edge positioned out of the duct of the fuselage and axially forward of a leading edge of the fuselage.

44. An aerial vehicle according to claim 43, wherein the canard wing includes a trailing edge positioned out of the duct of the fuselage and axially forward of the leading edge of the fuselage.

45. An aerial vehicle according to claim 43, wherein the at least one canard wing comprises four canard wings radially extending from the longitudinal axis of the fuselage.

46. An aerial vehicle according to claim 43, further comprising a central pod extending beyond a leading edge of the fuselage coaxially along the longitudinal axis and outer pods extending from the leading edge of the fuselage parallel with the longitudinal axis, and wherein the at least one canard wing comprises four canard wings radially extending with respect to the longitudinal axis from the central pod to the outer pods.

47. An aerial vehicle according to claim 46, wherein the outer pods contain fuel cells.

48. An aerial vehicle according to claim 47, wherein the fuel cells comprise batteries.

49. An aerial vehicle according to claim 46, wherein distal ends of the outer pods comprise landing gear.

50. An aerial vehicle according to claim 46, wherein the central pod contains an avionics bay.

51. An aerial vehicle according to claim 46, wherein the central pod contains a payload bay.

52. An aerial vehicle according to claim 46, wherein the central pod contains an actuator operatively connected to the rod of the rotor assemblies.

53. An aerial vehicle according to claim 30, wherein the fuselage includes an internal toroidal fuel bladder positioned against a leading edge of the fuselage.