Rotary wing vehicle

• US 9,434,471 B2
• Filed: 05/21/2013
• Issued: 09/06/2016
• Est. Priority Date: 04/14/2005
• 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
• Primary Examiner(s): Sanderson, Joseph W
• Application Number:
  US13/899,252
• Publication Number:
  US 20140091172A1
• Time in Patent Office: 1,204 Days
• US Class Current: 1/1
• CPC Class Codes: B64C 2027/8236 including pusher propellers
• CPC Class Codes: B64C 2027/8281 comprising horizontal tail planes
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64C 27/14 Direct drive between power plant and rotor hub
• CPC Class Codes: B64C 27/605 including swash plate, spider or cam mechanisms
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64C 7/00 Structures or fairings not otherwise provided for
• CPC Class Codes: B64U 10/13 Flying platforms
• 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 50/13 using external fans or propellers
• CPC Class Codes: B64U 50/19 using electrically powered motors
• 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. A rotary wing aircraft comprising

a first variable pitch rotor blade supported for rotation about a common rotor axis of rotation in a first rotor plane of rotation,

a second variable pitch rotor blade supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation,

a first blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the first rotor blade,

a second blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the second rotor blades,

a first pitch control linkage having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller so that displacement of the first pitch control linkage operates both the first blade pitch controller and second blade pitch controller at the same time, and

a first servo actuator located between the first rotor plane of rotation and the second rotor plane of rotation and coupled to the first pitch control linkage to operate the first pitch control linkage.

2. The rotary wing aircraft of claim 1, wherein displacement of the first pitch control linkage causes the first blade pitch controller to vary a cyclic pitch of the first rotor blade and causes the second blade pitch controller to vary a cyclic pitch of the second rotor blade.

3. A rotary wing aircraft comprising

a first variable pitch rotor blade supported for rotation about a common rotor axis of rotation in a first rotor plane of rotation,

a second variable pitch rotor blade supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation,

a first blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the first rotor blade,

a second blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the second rotor blades, and

a first pitch control linkage having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller so that displacement of the first pitch control linkage operates both the first blade pitch controller and second blade pitch controller at the same time,

wherein the first pitch control linkage is configured to tilt the first and second blade pitch controllers in different directions.

4. The rotary wing aircraft of claim 3, wherein the first pitch control linkage is a Z-link and the first end and second end cooperate to hold the first blade pitch controller and second blade pitch controller at a fixed-phase angle relative to each other.

5. The rotary wing aircraft of claim 3, wherein a fixed phase angle between a first blade pitch controller tilt axis and a second blade pitch controller tilt axis is between about 60 degrees and 120 degrees.

6. A rotary wing aircraft comprising

a first variable pitch rotor blade supported for rotation about a common rotor axis of rotation in a first rotor plane of rotation,

a second variable pitch rotor blade supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation,

a first blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the first rotor blade,

a second blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the second rotor blades,

a first pitch control linkage having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller so that displacement of the first pitch control linkage operates both the first blade pitch controller and second blade pitch controller at the same time, and

a second pitch control linkage interconnecting the first blade pitch controller and the second blade pitch controller to form a system of common pitch control linkages and the system of common pitch control linkages cooperate to control the cyclic pitch of the first and second rotor blades and a collective pitch of the first and second rotor blades.

7. A rotary wing aircraft comprising

a first variable pitch rotor blade supported for rotation about a common rotor axis of rotation in a first rotor plane of rotation,

a second variable pitch rotor blade supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation,

a first blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the first rotor blade,

a second blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the second rotor blades, and

a first pitch control linkage having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller so that displacement of the first pitch control linkage operates both the first blade pitch controller and second blade pitch controller at the same time,

wherein displacement of the first pitch control linkage causes the first blade pitch controller to operate along a first cyclic phase angle to vary the cyclic pitch of the first rotor blade and causes the second blade pitch controller to operate along a second cyclic phase angle to vary the cyclic pitch of the second rotor blade and the first cyclic phase angle of the first blade pitch controller is different from the second cyclic phase angle of the second blade pitch controller.

8. A rotary wing aircraft comprising

a first variable pitch rotor blade supported for rotation about a common rotor axis of rotation in a first rotor plane of rotation,

a second variable pitch rotor blade supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation,

a first blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the first rotor blade,

a second blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the second rotor blades, and

a first pitch control linkage having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller so that displacement of the first pitch control linkage operates both the first blade pitch controller and second blade pitch controller at the same time,

wherein the first pitch control linkage acts as an anti-rotation linkage and blocks the first and second blade pitch controllers from rotating about the common rotor axis of rotation.

9. A rotary wing aircraft comprising

a non-rotating structural backbone,

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

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

a first pitch linkage interconnecting the first blade pitch controller to the second blade pitch controller, and

a first servo actuator coupled to the non-rotating structural backbone and located between the first and second rotor planes of rotation,

wherein the first blade pitch controller and the second blade pitch controller are positioned to lie between the first rotor plane and second rotor plane in axially spaced-apart relation to one another and displacement of the first pitch linkage operates the first blade pitch controller and second blade pitch controller simultaneously.

10. A rotary wing aircraft comprising

a non-rotating structural backbone,

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

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

a first pitch linkage interconnecting the first blade pitch controller to the second blade pitch controller, and

an aerodynamic body shell supported by the non-rotating structural backbone and surrounding and the first pitch control linkage to minimize air resistance of the rotary wing aircraft.

11. A rotary wing aircraft comprising

a first variable pitch rotor blade supported for rotation about a common rotor axis of rotation in a first rotor plane of rotation and the first variable pitch rotor blade includes cyclic pitch control,

a second variable pitch rotor blade supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation and the second variable pitch rotor blade includes cyclic pitch control,

a first servo actuator located between the first rotor plane of rotation and the second rotor plane of rotation and configured to vary a pitch of the first rotor blade, and

a non-rotating structural backbone formed to include a hollow interior extending along the common rotor axis of rotation through the second rotor plane of rotation and the first servo actuator is coupled to the non-rotating structural backbone,

a first blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation for controlling a pitch of the first rotor blade and the first servo actuator is coupled to the first blade pitch controller by a first pitch linkage, and

an aerodynamic body shell coupled to the non-rotating structural backbone and arranged to surround the non-rotating structural backbone between the first rotor plane of rotation and the second rotor plane of rotation.

12. The rotary wing aircraft of claim 11, further comprising a power source located below the second rotor plane of rotation and configured to provide power to drive the first variable pitch rotor blade and the power is transmitted through the non-rotating structural backbone.

13. The rotary wing aircraft of claim 11, further comprising a power source located below the second rotor plane of rotation and configured to provide power to the first servo actuator and the power is transmitted through the non-rotation structural backbone.

14. The rotary wing aircraft of claim 11, further comprising a second blade pitch controller configured to vary a pitch of the second variable pitch rotor blade and a second servo actuator supported by the non-rotating structural backbone between the first rotor plane of rotation and the second rotor plane of rotation and coupled to the second blade pitch controller by a second pitch linkage and wherein the second variable pitch rotor blade includes cyclic pitch control and the first servo actuator and the second servo actuator cooperate to vary the pitch of the first and second rotor blades.

15. The rotary wing aircraft of claim 11, further comprising a second servo actuator coupled to the non-rotating structural backbone between the first rotor plane of rotation and the second rotor plane of rotation and a second pitch linkage interconnecting the second servo actuator and the second blade pitch controller to vary a pitch of the second rotor blade.

16. The rotary wing aircraft of claim 11, wherein the non-rotating structural backbone supports the first variable pitch rotor blade for rotation about the common rotor axis of rotation.

17. The rotary wing aircraft of claim 11, wherein power to drive the first variable pitch rotor blade about the common rotor axis of rotation is transmitted through the hollow interior of the non-rotating structural backbone.

18. The rotary wing aircraft of claim 11, further comprising a second blade pitch controller located between the first rotor plane of rotation and the second rotor plane of rotation and configured to control a pitch of the second rotor blade and the first pitch control linkage is coupled to the second blade pitch controller to cause the pitch of the first rotor blade and second rotor blade to be varied simultaneously.

19. The rotary wing aircraft of claim 11, wherein the aerodynamic body shell is fixed to the non-rotating structural backbone and is non-rotatable about the common rotor axis of rotation.

20. The rotary wing aircraft of claim 11, wherein the aerodynamic body shell is configured to reduce drag of the rotary wing aircraft in high speed flight.

21. The rotary wing aircraft of claim 11, further including a rearward facing propeller capable of creating a horizontal thrust force to push the rotary wing aircraft horizontally.

22. The rotary wing aircraft of claim 21, wherein the aerodynamic body shell is configured to reduce drag of the rotary wing aircraft in high speed flight.

23. A rotary wing aircraft comprising

a non-rotating structural backbone formed to include an interior space therein,

a first variable pitch rotor blade supported for rotation about a rotor axis of rotation in a first rotor plane of rotation and a first swashplate connected to the non-rotating structural backbone for controlling a cyclic pitch of the first rotor blade,

a second variable pitch rotor blade supported for rotation about the rotor axis of rotation in a second rotor plane of rotation and a second swashplate connected to the non-rotating structural backbone for controlling a cyclic pitch of the second rotor blade,

a power module located below the second rotor plane of rotation and configured to provide power to drive the first variable pitch rotor blade about the rotor axis of rotation, and

a first motor located below the second variable pitch rotor blade and coupled to the first variable pitch rotor blades by a rotating torque tube and the rotating torque tube is arranged to extend through the interior space of the non-rotating structural backbone,

wherein the power is transmitted through the interior space, the non-rotating structural backbone supports a majority of flight loads of the first variable pitch rotor blade and the rotating torque tube transmits rotational motion to drive the first variable pitch rotor blade about the rotor axis of rotation.

24. The rotary wing aircraft of claim 23, wherein the rotating torque tube is supported adjacent to the first variable pitch rotor blades by the non-rotating structural backbone.

25. The rotary wing aircraft of claim 23, wherein the non-rotating structural backbone supports horizontal flight loads generated by the first variable pitch rotor blade and stabilizes the rotation of the first variable pitch rotor blade about the rotor axis of rotation.

26. The rotary wing aircraft of claim 23, wherein the non-rotating structural backbone supports vertical flight loads generated by the first variable pitch rotor blade.

27. The rotary wing aircraft of claim 23, wherein the rotating torque tube supports vertical flight loads generated by the first variable pitch rotor blade.

28. The rotary wing aircraft of claim 23, further including a rearward facing propeller capable of creating a horizontal thrust force to push the rotary wing aircraft horizontally.

29. The rotary wing aircraft of claim 23, further including an aerodynamic body shell coupled to the non-rotating structural backbone and arranged to surround the non-rotating structural backbone between the first rotor plane of rotation and the second rotor plane of rotation and configured to reduce drag of the rotary wing aircraft in high speed flight.

30. A rotary wing aircraft comprising

a non-rotating structural backbone formed to include a space therein,

a first variable pitch rotor blade supported for rotation about a rotor axis of rotation in a first rotor plane of rotation and a first swashplate connected to the non-rotating structural backbone for controlling a cyclic pitch of the first variable pitch rotor blades,

a second variable pitch rotor blade supported for rotation about the rotor axis of rotation in a second rotor plane of rotation and a second swashplate connected to the non-rotating structural backbone for controlling a cyclic pitch of the second variable pitch rotor blades, and

a first motor located below the second rotor plane of rotation and coupled to the first variable pitch rotor blade to drive the first variable pitch rotor blade about the rotor axis of rotation, and

a second motor located below the second rotor plane of rotation and coupled to the second variable pitch rotor blade to drive the second variable pitch rotor blade about the rotor axis of rotation,

wherein power to drive the first variable pitch rotor blade about the rotor axis of rotation is transmitted from the first motor to the first variable pitch rotor blade by a rotating torque tube located in the space formed in the non-rotating structural backbone.

31. A rotary wing aircraft comprising

a non-rotating structural backbone formed to include a space therein,

a first variable pitch rotor blade supported for rotation about a rotor axis of rotation in a first rotor plane of rotation and a first swashplate connected to the non-rotating structural backbone for controlling a cyclic pitch of the first variable pitch rotor blades,

a second variable pitch rotor blade supported for rotation about the rotor axis of rotation in a second rotor plane of rotation and a second swashplate connected to the non-rotating structural backbone for controlling a cyclic pitch of the second variable pitch rotor blades, and

a first motor located below the second rotor plane of rotation and coupled to the first variable pitch rotor blade to drive the first variable pitch rotor blade about the rotor axis of rotation, and

a speed reduction system located adjacent to an upper end of the non-rotating structural backbone and arranged to interconnect the first variable pitch rotor blade and the torque tube,

wherein power to drive the first variable pitch rotor blade about the rotor axis of rotation is transmitted from the first motor to the first variable pitch rotor blade by a rotating torque tube located in the space formed in the non-rotating structural backbone.

32. The rotary wing aircraft of claim 31, further comprising an aircraft fuselage coupled to a lower end of the non-rotating structural backbone.

33. The rotary wing aircraft of claim 31, wherein the non-rotating structural backbone supports flight loads generated by the first variable pitch rotor blade and stabilizes the rotation of the first variable pitch rotor blade about the rotor axis of rotation.

34. A rotary wing aircraft comprising

a non-rotating structural backbone or mast extending in parallel relation to a rotor axis of rotation,

first variable pitch rotor blades supported for rotation about the rotor axis of rotation in a first rotor plane of rotation,

second variable pitch rotor blades supported for rotation about the rotor axis of rotation in a second rotor plane of rotation,

a first swashplate located between the first rotor plane of rotation and the second rotor plane of rotation for controlling the pitch of the first variable pitch rotor blades,

a second swashplate located between the first rotor plane of rotation and the second rotor plane of rotation for controlling the pitch of the second variable pitch rotor blades,

a plurality of first pitch control linkages coupled to the first swashplate so that displacement of the first pitch control linkages operates the first swashplate,

a plurality of second pitch control linkages coupled to the second swashplate so that displacement of the second pitch control linkage operates the second swashplate,

wherein the first swashplate and second swashplate are rotated about the rotor axis of rotation relative to each other by an angle so that the first control linkages and the second control linkages are interleaved around the circumference of the non-rotating backbone or mast and alternately connected to the first swashplate and the second swashplate thereby forming a compact installation.

35. The rotary wing aircraft of claim 34 further including servo actuators attached to linkages and the servo actuators are configured to lie adjacent to a longitudinally extending plane defined by the rotor axis of rotation and a longitudinal axis to reduce the forward facing surface area of the servo actuators and minimize aerodynamic drag of the rotary wing aircraft in high-speed forward flight.

36. The rotary wing aircraft of claim 35 further including a motor located below the second variable pitch rotor blades and a torque tube running inside the non-rotating backbone or mast for transmitting power between the motor and first rotor blades.

37. The rotary wing aircraft of claim 34 further including a streamlined mast shroud supported by the non-rotating backbone or mast and covering the servo actuators to minimize aerodynamic drag of the rotary wing aircraft in high-speed forward flight.

38. The rotary wing aircraft of claim 34 further including servo actuators located at a lower end of the non-rotating backbone or mast and pushrods connecting the servo actuators to the pitch control linkages, wherein the non-rotating backbone or mast is configured with internal passageways or conduits receptive to pushrods and operation of the pushrods within the internal passageways or conduits actuates the pitch control linkages and at least one of the first swashplate and the second swashplate.

39. The rotary wing aircraft of claim 34 further including a Z-link body and the Z-link body holds a first pitch control linkage in fixed relation to a second control linkage to form a Z-link and displacement of the Z-link parallel to axis of rotation operates first swashplate and second swashplate simultaneously.

40. The rotary wing aircraft of claim 39 wherein displacement of the Z-link parallel to axis of rotation causes first swashplate and second swashplate to simultaneously tilt in different directions separated by a differential phase angle of about 90 to 120 degrees to induce first variable pitch rotor blades and second variable pitch rotor blades to operate in phase with each other and produce power control forces.

41. The rotary wing aircraft of claim 34 further including servo actuators and the servo actuators are linear screwtype actuators each having a first end coupled to the non-rotating backbone or mast and a second end coupled to at least one of the first and second pitch control linkages for actuating at least one of the first swashplate and the second swashplate.

42. The rotary wing aircraft of claim 34, wherein the first swashplate and the second swashplate each include three swashplate arms and two of the swashplate arms of each of the first and second swashplates are located closer to each other than to the remaining swashplate arm of the respective swashplate to reduce the forward facing width of first swashplate and second swashplate and reduce aerodynamic drag in high-speed flight.

43. The rotary wing aircraft of claim 42, wherein the first swashplate and the second swashplate are rotated 180 degrees about the rotor axis of rotation.

44. The rotary wing aircraft of claim 34, further including a rearward facing propeller capable of creating a horizontal thrust force to push the rotary wing aircraft horizontally.

45. The rotary wing aircraft of claim 34, further including an aerodynamic body shell coupled to the non-rotating structural backbone or mast and arranged to surround the non-rotating structural backbone or mast between the first rotor plane of rotation and the second rotor plane of rotation and configured to reduce drag of the rotary wing aircraft in high-speed flight.