Rotary wing vehicle

• US 8,469,307 B2
• Filed: 10/11/2011
• Issued: 06/25/2013
• 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): Sanderson, Joseph W
• Application Number:
  US13/270,872
• Publication Number:
  US 20120025012A1
• Time in Patent Office: 623 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 27/10 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. A rotary wing aircraft comprising:

an airframe for supporting a plurality of rotor systems for rotation about a common axis of rotation;

a first rotor system of the plurality of rotor systems, the first rotor system including first variable pitch rotor blades supported for rotation about the common rotor axis of rotation in a first rotor plane of rotation and a first pitch controller for controlling the pitch of the first rotor blades;

a second rotor system of the plurality of rotor systems, the second rotor system including second variable pitch rotor blades supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation and a second blade pitch controller for controlling the pitch of the second rotor blades;

a first pitch control linkage located between the first rotor plane of rotation and the second rotor plane of rotation having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller;

wherein displacement of the first pitch control linkage operates both the first blade pitch controller and second blade pitch controller simultaneously;

further including a first servo actuator for operating the first pitch linkage; and

wherein the first servo actuator is located between the first rotor plane of rotation and second rotor plane of rotation.

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

3. The rotary wing aircraft of claim 1, wherein displacement of the first pitch control linkage causes the first blade pitch controller and second blade pitch controller to move parallel to the common axis of rotation.

4. The rotary wing aircraft of claim 1, wherein displacement of the first pitch control linkage causes the first blade pitch controller to tilt along a first pitch controller tilt axis perpendicular to the common axis of rotation and causes the second blade pitch controller to tilt along a second pitch controller tilt axis perpendicular to the common axis of rotation.

5. The rotary wing aircraft of claim 4, wherein the first pitch controller tilt axis and second pitch controller tilt axis are substantially parallel.

6. The rotary wing aircraft of claim 1, further including additional pitch control linkages to form a system of pitch control linkages located between the first rotor plane of rotation and the second rotor plane of rotation with each control linkage having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller, and

the system of pitch control linkages cooperate to control the pitch of the first and second rotor blades.

7. A rotary wing aircraft comprising:

an airframe for supporting a plurality of rotor systems for rotation about a common axis of rotation;

a first rotor system of the plurality of rotor systems, the first rotor system including first variable pitch rotor blades supported for rotation about the common rotor axis of rotation in a first rotor plane of rotation and a first pitch controller for controlling the pitch of the first rotor blades;

a second rotor system of the plurality of rotor systems, the second rotor system including second variable pitch rotor blades supported for rotation about the common rotor axis of rotation in a second rotor plane of rotation and a second blade pitch controller for controlling the pitch of the second rotor blades;

a first pitch control linkage located between the first rotor plane of rotation and the second rotor plane of rotation having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller;

wherein displacement of the first pitch control linkage operates both the first blade pitch controller and second blade pitch controller simultaneously;

further including additional pitch control linkages to form a system of pitch control linkages located between the first rotor plane of rotation and the second rotor plane of rotation with each control linkage having a first end coupled to the first blade pitch controller and a second end coupled to the second blade pitch controller;

the system of pitch control linkages cooperate to control the pitch of the first and second rotor blades; and

further including a plurality of servo actuators for operating the system of pitch control linkages and the plurality of servo actuators are located between the first rotor plane of rotation and second rotor plane of rotation.

8. The rotary wing aircraft of claim 7, wherein displacement of the first pitch control linkage causes the first blade pitch controller to vary the cyclic pitch of the first rotor blades and causes the second blade pitch controller to vary the cyclic pitch of the second rotor blades.