ROTARY WING VEHICLE

• US 20110006166A1
• Filed: 08/31/2010
• Published: 01/13/2011
• Est. Priority Date: 04/14/2004
• Status: Active Grant

• Current Assignee: David J. Arlton, Paul E. Arlton
• Original Assignee: David J. Arlton, Paul E. Arlton
• Inventors: ARLTON, Paul E., Arlton, David J.
• Granted Patent: US 8,042,763 B2
• Time in Patent Office: Days
• US Class Current: 244/7.A
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64C 27/22 Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64U 10/13 Flying platforms
• CPC Class Codes: B64U 10/17 Helicopters flying platforms B64U10/13
• CPC Class Codes: B64U 20/40 Modular UAVs
• CPC Class Codes: B64U 20/50 Foldable or collapsible UAVs with frangible components B64U20/30
• CPC Class Codes: B64U 2201/10 autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep
• CPC Class Codes: B64U 30/16 movable along the UAV body
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/21 Rotary wings
• CPC Class Codes: B64U 50/11 using internal combustion piston engines
• CPC Class Codes: B64U 50/13 using external fans or propellers
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 50/32 generated by fuel cells
• CPC Class Codes: B64U 70/20 for releasing or capturing UAVs in flight by another aircraft
• CPC Class Codes: B64U 80/60 by wearable objects, e.g. garments or helmets
• CPC Class Codes: B64U 80/70 in containers B64U80/60 takes precedence
• CPC Class Codes: B64U 80/84 : Waterborne vehicles

Abstract

A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

Claims

1-11. -11. (canceled)

12. A rotary wing aircraft comprising

first and second counter-rotating rotors rotatable about a common rotor axis, each rotor having variable pitch rotor blades,

a flight control system having at least one electronic signal processing device for processing flight control commands, a first swashplate for controlling the pitch of the first rotor blades, a second swashplate for controlling the pitch of the second rotor blades and a servo actuator operably connected to both the first and second swashplates, and

electronic command signal means for controlling the servo actuator

to control the blade pitch of both rotors in unison.

13. The rotary wing aircraft of claim 12, wherein the means for controlling the servo actuator includes a command signal controller, and the swashplates are positioned to lie axially between the first and second rotor systems.

14. The rotary wing aircraft of claim 13, further comprising a second servo actuator, and wherein the command signal controller is connected to the first and second servo actuators to generate electronic signals to the first and second servo actuators to vary the blade pitch of both rotor systems.

15. The rotary wing aircraft of claim 13, further comprising a third servo actuator, and wherein the command signal controller is connected to the first, second, and third servos to generate electronic signals to the first, second and third servo actuators to vary cyclic and collective blade pitch of both rotor systems.

16. The rotary wing aircraft of claim 13, further comprising first and second motors coupled to the first and second rotors, respectively, and wherein the command signal controller is connected to the first motor and second motors to generate electronic torque control signals to at least one of the first motor and second motor to vary the speed of at least one of the first and second rotors to control at least one of total thrust along the common rotor axis and total torque about the common rotor axis.

17. The rotary wing aircraft of claim 16, further comprising a least one motor to drive one of the first and second rotors, a power module to provide power to the motor and a non-rotating structural backbone to support the motor, power module and first and second rotors along the axis of rotation, wherein the power module and motor are coupled to the non-rotating structural backbone in spaced apart relation to locate one of the first and second rotor systems therebetween and a cross section of the non-rotating structural backbone includes open areas arranged to extend along a length of the aircraft such that energy from the power module is conducted to the motor across the rotor system through the structural backbone.

18. The rotary wing aircraft of claim 12, further comprising a first and a second module coupled to a non-rotating structural backbone, and wherein the first module and the second rotor system are positioned to lie in spaced-apart relation to one another to locate the first rotor system therebetween, and the first module and the second module are positioned to lie in spaced apart relation to one another to locate the second rotor system therebetween.

19. The rotary wing aircraft of claim 12, wherein the first and second swashplates are operably connected by a common swashplate linkages to move in unison.

20. The rotary wing aircraft of claim 19, wherein the first and second swashplates are actuated by at most two servo actuators which tilt the first and second swashplates in unison.

21. The rotary wing aircraft of claim 19, wherein the first and second swashplates are actuated by at most three servo actuators and the three servo actuators control cyclic blade pitch by tilting the first and second swashplates in unison and collective blade pitch by translating the first and second swashplates in unison parallel to the rotor axis.

22. The rotary wing aircraft of claim 12, further comprising electronic control signals for varying the speed of rotation of the first and second rotors, and wherein altitude control of the rotary wing aircraft is accomplished by varying the speed of the first and second rotors substantially in unison.

23. The rotary wing aircraft of claim 22, further comprising electronic control signals for varying the speed of rotation of the first and second rotors, and wherein rotational control of the rotary wing aircraft about the common rotor axis is accomplished by varying the speed of the first and second rotors in opposition to each other.

24. The rotary wing aircraft of claim 22, wherein the common rotor axis is substantially vertical during flight.

25. The rotary wing aircraft of claim 22, wherein the common rotor axis is substantially horizontal during flight.

26-55. -55. (canceled)

56. A rotary wing aircraft comprising

a non-rotating structural backbone,

a first rotor system coupled to the non-rotating structural backbone, the first rotor system including first variable pitch rotor blades supported for rotation in a first rotor plane about an axis of rotation, and a first blade pitch controller for varying the cyclic pitch of the first rotor blades,

a second rotor system coupled to the non-rotating structural backbone, the second rotor system including second variable pitch rotor blades supported for rotation in a second rotor plane about the axis of rotation and a second blade pitch controller for varying the cyclic pitch of the second rotor blades, and

at least one servo actuator located between the first and second rotor planes and operably connected to the first and the second blade pitch controllers to actuate the first and second blade pitch controllers.

57. The rotary wing aircraft of claim 56, further including a first motor for driving the first rotor blades about the axis of rotation and a second motor for driving the second rotor blades about the axis of rotation wherein the first motor and first pitch controller are positioned to lie in spaced-apart relation to one another to locate the first rotor plane therebetween, and the second motor and second blade pitch controller are positioned to lie in spaced-apart relation to one another to locate the second rotor plane therebetween.

58. The rotary wing aircraft of claim 56, further including a first motor for driving the first rotor blades about the axis of rotation and a second motor for driving the second rotor blades about the axis of rotation wherein the first motor is positioned to lie on an inflow side of the second rotor system and the second motor is positioned to lie on an outflow side of the first rotor system.

59. A rotary wing aircraft comprising

a non-rotating structural backbone,

a first rotor system coupled to the non-rotating structural backbone including first variable pitch rotor blades supported by a first rotor shaft for rotation about an axis of rotation in a first rotor plane and controlled by a first blade pitch controller which includes cyclic pitch control,

a second rotor system coupled to the non-rotating structural backbone including second variable pitch rotor blades supported by a second rotor shaft for rotation about the axis of rotation in a second rotor plane and controlled by a second blade pitch controller which includes cyclic pitch control, the second rotor plane being positioned to lie in axially spaced apart relation to the first rotor plane along the axis of rotation,

wherein the first blade pitch controller is coupled to the non-rotating structural backbone so that neither the first rotor shaft nor the second rotor shaft extends through the first blade pitch controller.

60. The rotary wing aircraft of claim 59, wherein the first blade pitch controller and second blade pitch controller are connected by a common pitch linkage and operation of the common pitch linkage operates the first blade pitch controller and second blade pitch controller simultaneously.

61. The rotary wing aircraft of claim 59, wherein the first blade pitch controller is a first swashplate surrounding the non-rotating structural backbone and the first swashplate is axially spaced apart along the axis of rotation from the first rotor plane.

62. The rotary wing aircraft of claim 59, further including a first motor fixed to the non-rotating structural backbone and operably connected to the first rotor shaft by a first drive gear fixed to the first rotor shaft, and the diameter of the first blade pitch controller is smaller than the diameter of the first drive gear.

63. The rotary wing aircraft of claim 59, further including a first motor fixed to the non-rotating structural backbone to drive the first rotor blades about the axis of rotation, and the first motor and first blade pitch controller are positioned to lie on opposite sides of the first rotor plane.

64. The rotary wing aircraft of claim 59, wherein the second blade pitch controller is coupled to the non-rotating structural backbone so that neither the first rotor shaft nor the second rotor shaft extends parallel to the axis of rotation through the second blade pitch controller.

65. The rotary wing aircraft of claim 64, wherein the second blade pitch controller is a second swashplate surrounding the non-rotating structural backbone and the second swashplate is axially spaced apart along the axis of rotation from the second rotor plane.

66. The rotary wing aircraft of claim 64, further including a second motor fixed to the non-rotating structural backbone to drive the second rotor blades about the axis of rotation, and the second motor and second blade pitch controller are positioned to lie on opposite sides of the second rotor plane.

67. The rotary wing aircraft of claim 64, further including a second motor fixed to the non-rotating structural backbone to drive the second rotor blades about the axis of rotation, and the second motor and second blade pitch controller are positioned to lie on opposite sides of the second rotor plane.

68. A rotary wing aircraft comprising

a non-rotating structural backbone,

a first rotor system coupled to the non-rotating structural backbone, the first rotor system including first variable pitch rotor blades supported for rotation in a first rotor plane about an axis of rotation, and a first blade pitch controller coupled to the non-rotating structural backbone,

a second rotor system coupled to the non-rotating structural backbone, the second rotor system including second variable pitch rotor blades supported for rotation in a second rotor plane about the axis of rotation, and a second blade pitch controller coupled to the non-rotating structural backbone, and

a first common pitch linkage connecting the first pitch controller to the second pitch controller,

wherein the first pitch controller and second pitch controller are positioned to lie between the first rotor plane and second rotor plane in axially spaced apart relation to each other and displacement of the first common pitch linkage operates the first pitch controller and second pitch controller simultaneously.

69. The rotary wing aircraft of claim 68 further including a first pitch servo actuator connected to the first common pitch linkage and operation of the first pitch servo actuator operates both the first pitch controller and second pitch controller simultaneously through the first common pitch linkage.

70. The rotary wing aircraft of claim 69 further including a plurality of common pitch linkages connecting the first pitch controller to the second pitch controller, and a plurality of servo actuators connected to the plurality of common pitch linkages, and operation of at least one of the servo actuator operates both the first pitch controller and second pitch controller simultaneously through a common pitch linkage.

71. A rotary wing aircraft comprising

a non-rotating structural backbone,

a first rotor system coupled to the non-rotating structural backbone, the first rotor system including first variable pitch rotor blades supported for rotation about an axis of rotation by a first rotor shaft and controlled by a first swashplate including cyclic pitch control, and

a second rotor system coupled to the non-rotating structural backbone, the second rotor system including second variable pitch rotor blades supported for rotation about the axis of rotation by a second rotor shaft and controlled by a second swashplate including cyclic pitch control, the second rotor shaft being positioned to lie in axially spaced apart relation to the first rotor shaft along the axis of rotation,

wherein the first swashplate and the second swashplate surround the non-rotating structural backbone and the non-rotating structural backbone forms a narrow conduit through the first swashplate and the second swashplate to pass electrical or mechanical signals through at least one of the first swashplate and second swashplate.

72. The rotary wing aircraft of claim 71, further including a first power module and a first motor fixed to the non-rotating structural backbone for driving the first rotor blades about the axis of rotation and energy from the first power module is conducted through the first swashplate by way of electrical wiring or hoses running through the non-rotating structural backbone to power the first motor.

73. The rotary wing aircraft of claim 71, further including a control module and a first servo actuator for actuating the first pitch controller and a control signal from the control module is conducted through the first swashplate to the servo actuator by way of electrical wiring running through the non-rotating structural backbone.

74. The rotary wing aircraft of claim 71, wherein the non-rotating structural backbone is less than about 2½

inches (6.35 cm) in diameter.

75. The rotary wing aircraft of claim 71, wherein the non-rotating structural backbone is less than about 0.5 inches (12.5 mm) in diameter.

76. The rotary wing aircraft of claim 71, wherein the first rotor blades include a first rotor blade span measured across the tips of the first rotor blades, the second rotor blades include a second rotor blade span measured across the tips of the second rotor blades, and the diameter of the non-rotating structural backbone is less than about 10% of the blade span of one of the first and second rotor blades.

77. The rotary wing aircraft of claim 71, wherein the non-rotating structural backbone is substantially vertical during flight.

78. The rotary wing aircraft of claim 71, wherein the non-rotating structural backbone is substantially horizontal during flight.