A rotating wing aircraft has a rotating fuselage and wings. The aircraft is configured to rotate with the air passing over the wings because of the rotation providing the lift needed to keep the aircraft aloft. The wings have rudders coupled to them, such as at the tips of the wings, to provide for
A rotating wing aircraft has a rotating fuselage and wings. The aircraft is configured to rotate with the air passing over the wings because of the rotation providing the lift needed to keep the aircraft aloft. The wings have rudders coupled to them, such as at the tips of the wings, to provide force for laterally moving the aircraft. The aircraft may be able to remain airborne by hovering for a long period of time, on the order of days. Power for the aircraft may be provided by a central diesel electric generator, which provides power for electric motors that turn propellers that are on the wings. The aircraft may be used for any of a variety of applications, such as for surveillance, communications, or as a radar platform.
대표청구항▼
What is claimed is: 1. An aircraft comprising: a central rotating fuselage; at least two high aspect ratio wings attached to the central fuselage; respective rudders coupled to the wings; and a propulsion system configured to rotate the fuselage and the wings substantially within a plane defined by
What is claimed is: 1. An aircraft comprising: a central rotating fuselage; at least two high aspect ratio wings attached to the central fuselage; respective rudders coupled to the wings; and a propulsion system configured to rotate the fuselage and the wings substantially within a plane defined by the wings, thereby enabling the wings to generate lift; wherein the aircraft has a wingspan of at least about 6 meters; wherein the rudders are wing tip rudders at distal ends of the wings, away from the fuselage; and wherein the wing tip rudders produce force for lateral movement of the aircraft. 2. The aircraft of claim 1, wherein the aircraft has a wingspan of at least about 30 meters. 3. The aircraft of claim 1, wherein the aircraft has a wingspan of at least about 60 meters. 4. The aircraft of claim 1, wherein the at least two wings includes at least three wings. 5. The aircraft of claim 1, wherein the at least two wings includes at least four wings. 6. The aircraft of claim 1, wherein the wings are axisymmetrically located about the fuselage. 7. The aircraft of claim 1, wherein the wing tip rudders are hingedly coupled to the distal ends of the wings. 8. The aircraft of claim 1, wherein the wing tip rudders include actuatable tabs to control the angles of the rudders relative to the wings. 9. The aircraft of claim 1, further comprising a control system for cyclically positioning the rudders relative to the wings, to control lateral movement of the aircraft. 10. The aircraft of claim 1, wherein the propulsion system includes a propeller mechanically coupled to each of the wings. 11. The aircraft of claim 10, wherein the propulsion system further includes engines operatively coupled to respective of the propellers, to turn the propellers to cause rotation of the wings and the fuselage. 12. The aircraft of claim 10, wherein the propulsion system further includes respective electric motors coupled to the propellers to turn the propellers. 13. The aircraft of claim 12, wherein the propulsion system includes a generator that is operatively coupled to the electric motors. 14. The aircraft of claim 13, wherein the generator is part of a diesel electric generator. 15. The aircraft of claim 1, wherein the wings each include: an inboard support that is coupled to the fuselage and that is substantially not lift producing; and an outboard lift-producing region; wherein the inboard support and the outboard lift-producing region of each wing are substantially co-planar. 16. The aircraft of claim 15, wherein the outboard region is less than half of a length of the wing. 17. The aircraft of claim 15, wherein the outboard region is less than one-third of a length of the wing. 18. The aircraft of claim 15, wherein the outboard region is free to rotate relative to the inboard support substantially about an axis along a length of the wing, substantially without mechanical constraint. 19. The aircraft of claim 1, wherein the fuselage houses one or more sensors. 20. The aircraft of claim 1, further comprising a radar system coupled to the fuselage. 21. The aircraft of claim 20, wherein the radar system includes a radar dome that is located above the wings. 22. The aircraft of claim 1, wherein the fuselage includes a de-spun section that rotates at a different rate than the wings. 23. The aircraft of claim 22, wherein the de-spun section is substantially non-rotational. 24. The aircraft of claim 22, wherein the fuselage includes a de-spin motor that is mechanically coupled to the de-spun section for controlling the rotation rate of the de-spun section. 25. The aircraft of claim 1, wherein the wings each include respective ailerons. 26. The aircraft of claim 1, wherein each of the wings has a length of at least about 15 meters. 27. An aircraft comprising: a central rotating fuselage; at least two wings attached to the central fuselage; a propulsion system configured to rotate the fuselage and the wings substantially within a plane defined by the wings, thereby enabling the wings to generate lift; wherein the propulsion system includes propellers coupled to the wings to rotate the aircraft; wherein the wings each include: an inboard support that is coupled to the fuselage and that is substantially not lift producing; and an outboard lift-producing region; and wherein the inboard support and the outboard lift-producing region of each wing are substantially co-planar; and wherein the outboard region of each wing is free to rotate relative to the inboard support, about an axis along a length of the wing, substantially without mechanical constraint. 28. The aircraft of claim 27, wherein the outboard region is less than half of a length of the wing. 29. The aircraft of claim 27, wherein the outboard region is less than one-third of a length of the wing. 30. The aircraft of claim 27, wherein the propellers are coupled to the inboard supports. 31. The aircraft of claim 27, wherein the aircraft has a wingspan of at least about 6 meters. 32. The aircraft of claim 27, wherein the aircraft has a wingspan of at least about 30 meters. 33. The aircraft of claim 27, wherein the propellers are mounted inboard of the distal tips of the wings, such that the propellers encounter an effective airspeed less than an effective airspeed encountered at the distal tips of the wings. 34. The aircraft of claim 27, further comprising wing tip rudders at distal tips of the wings, away from the fuselage; wherein the wing tip rudders are configured to be cyclically tilted relative to the wings as the wings are rotated, to thereby produce force for lateral movement of the aircraft. 35. The aircraft of claim 27, wherein the propellers are mounted on the inboard supports of the wings. 36. The aircraft of claim 27, wherein the propulsion system further includes engines operatively coupled to respective of the propellers, to turn the propellers to cause rotation of the wings and the fuselage. 37. The aircraft of claim 27, wherein the propulsion system further includes respective electric motors coupled to the propellers to turn the propellers. 38. The aircraft of claim 37, wherein the propulsion system includes a generator that is operatively coupled to the electric motors. 39. The aircraft of claim 38, wherein the generator is part of a diesel electric generator. 40. An aircraft comprising: a central rotating fuselage; at least two wings attached to the central fuselage; and a propulsion system configured to rotate the fuselage and the wings substantially within a plane defined by the wings, thereby enabling the wings to generate lift; wherein the propulsion system includes: propellers coupled to the wings to rotate the aircraft; electric motors coupled to respective of the propellers to turn the propellers; and at least one generator coupled to the motors, to provide power to the motors. 41. The aircraft of claim 40, wherein the electric motors are in the wings; and wherein the at least one generator is in the central fuselage. 42. The aircraft of claim 40, wherein the at least one generator includes a pair of generators in the central fuselage. 43. The aircraft of claim 42, wherein rotation axes of the generators are oriented in substantially opposite directions. 44. The aircraft of claim 40, wherein the aircraft has a wingspan of at least about 6 meters. 45. The aircraft of claim 40, wherein the aircraft has a wingspan of at least about 30 meters. 46. An aircraft comprising: a central rotating fuselage; at least two wings attached to the central fuselage; rudders mechanically coupled to the wings to exert a lateral force on the aircraft; a propulsion system configured to rotate the fuselage and the wings substantially within a plane defined by the wings, thereby enabling the wings to generate lift; and a control system coupled to the rudders to cyclically position the rudders; wherein the control system includes magnetic induction coils located in the wings, to sense orientation of the wings. 47. The aircraft of claim 46, wherein the rudders are at distal ends of the wings. 48. The aircraft of claim 46, wherein the rudders are hingedly coupled to the wings. 49. The aircraft of claim 27, wherein the aircraft has a wingspan of at least about 6 meters.
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이 특허에 인용된 특허 (1)
Crimmins ; Jr. Arthur G. (Bozman MD), Cyclorotor composite aircraft.
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