AUTOGYRO AIR VEHICLE

• US 20110139928A1
• Filed: 12/13/2010
• Published: 06/16/2011
• Est. Priority Date: 12/12/2009
• Status: Active Grant

• Current Assignee: Air Support Technologies LLC
• Original Assignee: Heliplane LLC
• Inventors: Morris, John William, Jarnot, Charles A.
• Granted Patent: US 8,540,183 B2
• Time in Patent Office: Days
• US Class Current: 244/1.TD
• CPC Class Codes: B64C 2025/325 specially adapted for helicopters
• CPC Class Codes: B64C 25/52 Skis or runners
• CPC Class Codes: B64C 27/02 Gyroplanes
• CPC Class Codes: B64C 27/021 Rotor or rotor head construction for helicopters B64C27/32
• CPC Class Codes: B64C 27/025 Rotor drives, in particular for taking off; Combination of autorotation rotors and driven rotors
• CPC Class Codes: B64D 3/00 Aircraft adaptations to facilitate towing or being towed B64D39/00 takes precedence
• CPC Class Codes: B64D 39/00 Refuelling during flight filling or emptying fuel tanks B64D37/14
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/11 Autogyros
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 2201/20 Remote controls
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/291 Detachable rotors or rotor supports
• CPC Class Codes: B64U 30/292 Rotors or rotor supports specially adapted for quick release
• CPC Class Codes: B64U 30/40 Empennages, e.g. V-tails foldable or collapsible UAVs B64U20/50
• CPC Class Codes: B64U 80/82 Airborne vehicles
• CPC Class Codes: G05D 1/102 specially adapted for vertical take-off of aircraft

Abstract

An unmanned, towable aerovehicle is described and includes a container or frame to hold or support cargo, at least one and, in some examples, a plurality of autogyro assemblies connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container or frame includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly. In an example, the autogyro assembly includes a mast extending from the container, a rotatable hub on an end of the mast, and a plurality of blades connected to the hub for rotation to provide lift to the vehicle. In an example, an electrical motor rotates the blades prior to lift off to assist in take off. In an example, the electrical motor does not have enough power to sustain flight of the vehicle. The aerovehicle can further include plurality of autogyro assemblies to assist in flight. The aerovehicle can include surfaces that provide lift or control to assist in the flight profile of the aerovehicle.

Claims

1. An aerovehicle, comprising:

a frame, wherein the frame is towable in flight;

a plurality of autogyro assemblies connected to the frame; and

a controller to control operation the plurality of autogyro assemblies for unmanned flight.

2. The aerovehicle of claim 1, wherein the frame includes a connection to connect to a powered aircraft to provide forward motive force to power the plurality of autogyro assemblies.

3. The aerovehicle of claim 2, wherein each of the plurality of autogyro assemblies comprises a mast extending from the frame, a rotatable hub on an end of the mast, and a plurality of airfoil blades connected to the hub.

4. The aerovehicle of claim 3, wherein each of the plurality of autogyro assemblies comprise a motor to rotate the blades prior to lift off to assist in take off, and wherein the motor does not have enough power to lift the frame from the ground.

5. The aerovehicle of claim 4, wherein the controller is to sense forward motion to control the plurality of autogyro assemblies.

6. The aerovehicle of claim 5, wherein the controller is to receive signal from a propulsion device and to control the plurality of autogyro assemblies using the received signal.

7. The aerovehicle of claim 6, wherein the controller is to control the rotational speed of the hub.

8. The aerovehicle of claim 3, wherein the plurality of autogyro assemblies comprises actuators to control angle of the plurality of airfoil blades, and wherein the controller controls the actuators.

9. The aerovehicle of claim 1, wherein the frame comprises an enclosure to hold cargo, a rear stabilizer, and an undercarriage to support the container when on the ground.

10. The aerovehicle of claim 9, wherein the undercarriage includes a trolley that contacts the ground to provide mobility and is removable from the container.

11. The aerovehicle of claim 1, wherein the controller is to issue control signals to position airfoil blades for different stages of flight.

12. The aerovehicle of claim 11, wherein the controller is to issue a flight control signal to set the airfoil blades for flight.

13. The aerovehicle of claim 12, wherein the controller is to issue a takeoff control signal to set the airfoil blades for takeoff, wherein the angle of incidence of the airfoil blades is greater at takeoff than at flight.

14. The aerovehicle of claim 13, wherein the controller is to issue a prerotation control signal to set the airfoil blades for pre-takeoff, wherein the angle of incidence of the airfoil blades is greater at takeoff and flight than at prerotation.

15. The aerovehicle of claim 14, wherein the controller is to issue a landing control signal to set the airfoil blades for landing, wherein the angle of incidence of the airfoil blades is greatest at landing.

16. The aerovehicle of claim 1, wherein the controller is to control a propulsion system that has sufficient thrust to assist in a cargo laden flight and an essentially cargo-free flight and does not have enough thrust to fly a frame supporting cargo.

17. The aerovehicle of claim 16, wherein the propulsion system includes an on-board motor, a drive shaft connected to the motor and extending outside the frame, and a propeller connected to the drive shaft.

18. The aerovehicle of claim 1, wherein the frame includes a tow line connection that releasably holds a tow line.

19. The aerovehicle of claim 18, wherein the tow line includes a mechanical component to transfer trust from a towing aircraft to the frame and an electrical component that transfers electrical signals from the towing aircraft to the controller.

20. The aerovehicle of claim 1, wherein the controller is to receive signals from other controllers of nearby aerovehicles.

21. The aerovehicle of claim 1, wherein the frame includes a moveable vertical stabilizer.

22. The aerovehicle of claim 21, wherein the frame includes at least one horizontal stabilizer.

23. The aerovehicle of claim 1, wherein the frame includes a first horizontal stabilizer extending outwardly of an intermediate portion of the frame in a first direction and a second horizontal stabilizer extending outwardly from the intermediate portion of the frame in a second direction.

24. The aerovehicle of claim 1, wherein the frame includes a liquid tank.

25. The aerovehicle of claim 1, wherein the liquid tank is to provide in-flight refueling to an aircraft.

26. The aerovehicle of claim 1, wherein the liquid tank includes a drop system to release the liquid from the tank.