TOWABLE AIR VEHICLE

• US 20130008998A1
• Filed: 05/21/2010
• Published: 01/10/2013
• Est. Priority Date: 05/22/2009
• Status: Active Grant

• Current Assignee: Air Support Technologies LLC
• Original Assignee: Heliplane LLC
• Inventors: Morris, John William, Jarnot, Charles
• Granted Patent: US 8,366,037 B2
• Time in Patent Office: Days
• US Class Current: 244/3
• CPC Class Codes: B64C 27/02 Gyroplanes
• CPC Class Codes: B64C 39/024 of the remote controlled vehicle type, i.e. RPV
• CPC Class Codes: B64D 3/00 Aircraft adaptations to facilitate towing or being towed B64D39/00 takes precedence
• CPC Class Codes: B64U 10/10 Rotorcrafts
• CPC Class Codes: B64U 10/11 Autogyros
• CPC Class Codes: B64U 10/60 Tethered aircraft
• 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 30/29 Constructional aspects of rotors or rotor supports; Arrangements thereof
• CPC Class Codes: B64U 50/10 Propulsion rotors specially adapted for rotorcraft or VTOL B64U30/20

Abstract

An unmanned, towable aerovehicle is described and includes a container to hold cargo, an autogyro assembly connected to the container and to provide flight characteristics, and a controller to control operation the autogyro assembly for unmanned flight. The container 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. The electrical motor does not have enough power to sustain flight of the vehicle.

Claims

1. An aerovehicle, comprising:

a flight body;

an autogyro assembly connected to the flight body; and

a controller to control operation the autogyro assembly for unmanned flight.

2. The aerovehicle of claim 1, wherein the flight body includes a connection to connect to a powered aircraft to provide forward motive force to power the autogyro assembly.

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

4. The aerovehicle of claim 3, wherein the autogyro assembly comprises 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 power the aerovehicle through takeoff absent a further motive force.

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

6. The aerovehicle of claim 5, wherein the controller is to receive signal from a propulsion device and to control the autogyro assembly 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 autogyro assembly 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 flight body comprises a container 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 15, wherein the controller sets the landing angle of incidence to 45 degrees or greater and sets the flight angle of incidence to less 30 degrees.

17. 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 flight body full of cargo.

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

19. The aerovehicle of claim 1, wherein the flight body includes a tow line connection that releasably holds a tow line.

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

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

22. The aerovehicle of claim 21, wherein the controller is to act as a master controller and issue control signals to nearby aerovehicles.

23. The aerovehicle of claim 1, wherein the a plurality of the nearby aerovehicles are towed by a single towing aircraft.

24. The aerovehicle of claim 1, wherein the flight body includes sensors that produce signals, and wherein controller receives the signals and applies instructions to the signals to output control signals.

25. The aerovehicle of claim 24, wherein the sensors include weight sensors on flight body to determine at least one of the weight and center of gravity of the flight body and cargo, and wherein the controller issues a control signal to adjust the position of the autogyro assembly on the flight body.

26. The aerovehicle of claim 25, wherein the controller issues signals to control actuators that adjust a longitudinal position of the autogyro assembly, a lateral position of the autogyro assembly, or both.

27. The aerovehicle of claim 1, wherein the controller is to receive a forward air speed indicator to control the speed of the flight body and keep the speed below a never-exceed velocity.

28. The aerovehicle of claim 1, wherein the controller is to receive rotation speed signal from the autogyro assembly and issue a brake signal if the rotational speed exceeds a safe rotational speed.

29. The aerovehicle of claim 1, wherein the controller is to determine a stall and to automatically release a tow line if a stall is determined.

30. The aerovehicle of claim 1, wherein the controller is to control flight after release from a motive device and calculate a flight path based on current sensed signals and a programmed destination.

31. The aerovehicle of claim 1, further comprising a propulsion system and wherein the controller controls operation of the propulsion system.