Rotary wing vehicle

• US 8,042,763 B2
• Filed: 08/31/2010
• Issued: 10/25/2011
• 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.
• Primary Examiner(s): MICHENER, JOSHUA J
• Application Number:
  US12/872,622
• Publication Number:
  US 20110006166A1
• Time in Patent Office: 420 Days
• Field of Search: 244/17.11, 244/17.13, 244/17.21, 244/17.23, 244/17.25, 416/124, 416/125, 416/127, 416/129, 416/130, 446/36, 446/37
• US Class Current: 244/17.23
• CPC Class Codes: B64C 27/22 Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
• 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. 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.

2. The rotary wing aircraft of claim 1, 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.

3. The rotary wing aircraft of claim 1, 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.

4. The rotary wing aircraft of claim 1, 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.

5. The rotary wing aircraft of claim 1, 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.

6. The rotary wing aircraft of claim 1, 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.

7. The rotary wing aircraft of claim 6, 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.

8. The rotary wing aircraft of claim 6, 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.

9. The rotary wing aircraft of claim 6, 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.