TOWABLE AIR VEHICLE

• US 20120091259A1
• Filed: 08/22/2011
• Published: 04/19/2012
• Est. Priority Date: 08/23/2010
• Status: Active Grant

• Current Assignee: Air Support Technologies LLC
• Original Assignee: Heliplane LLC
• Inventors: Morris, John William, Jarnot, Charles A.
• Granted Patent: US 8,646,719 B2
• Time in Patent Office: Days
• US Class Current: 244/17.13
• CPC Class Codes: B64C 19/00 Aircraft control not otherwise provided for
• CPC Class Codes: B64C 27/02 Gyroplanes
• CPC Class Codes: B64D 3/00 Aircraft adaptations to facilitate towing or being towed B64D39/00 takes precedence
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/291 Detachable rotors or rotor supports
• CPC Class Codes: B64U 80/82 Airborne vehicles

Abstract

An unmanned, towable air vehicle is described and includes electronic sensors to increase the detection range relative to the horizon detection limitations of a surface craft, an autogyro assembly to provide lift, and a controller to control operation the autogyro assembly for unmanned flight. A forward motive force powers the autogyro assembly to provide lift. 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 in an example.

Claims

1. An air vehicle to be towed by a surface vehicle, comprising:

an unmanned flight body;

an autogyro assembly connected to the flight body, the autogyro being adapted for unmanned flight;

a controller to control operation the autogyro assembly for unmanned flight; and

a sensor to detect other objects adjacent the air vehicle.

2. The vehicle of claim 1, wherein the sensor is to provide electronic protection to the surface vehicle.

3. The vehicle of claim 1, wherein the sensor increases a sensor range by at least 3 times relative to a horizon detection distance.

4. The vehicle of claim 1, wherein the flight body includes a connection to a tow line that is connected to a winch that can play out the line and is mounted to the surface vehicle and wherein at least one of the winch, the surface vehicle or both provide forward motive force to the autogyro assembly.

5. The vehicle of claim 4, wherein the flight body includes an electrical connection to connect to a powered surface vehicle to provide electrical energy to the controller and the sensor.

6. The vehicle of claim 1, 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.

7. The vehicle of claim 6, 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 air vehicle through takeoff absent a further motive force.

8. The vehicle of claim 6, wherein the controller is to sense forward motion to control the autogyro assembly.

9. The vehicle of claim 8, wherein the controller is to receive signal from a propulsion device and to control the autogyro assembly using the received signal.

10. The vehicle of claim 9, wherein the controller is to control the rotational speed of the hub, wherein the autogyro assembly comprises actuators to control angle of the plurality of airfoil blades, and wherein the controller controls the actuators, and wherein the flight body comprises a container to house the controller and the sensor, a flight stabilizer, and an undercarriage to support the container when on the ground.

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

12. The vehicle of claim 1, wherein the controller is to receive signals from other controllers of nearby air vehicles.

13. The vehicle of claim 4, wherein the winch comprises:

a winch block;

a pivot member in contact with the winch block;

a guide funnel in contact with the pivot member; and

a

a tow line, in contact with at least one of the pivot member, guide funnel, winch block and the air vehicle.

14. A detection system comprising:

a towing vehicle; and

an air vehicle in communication with the towing vehicle, the air vehicle comprising;

a flight body;

an autogyro assembly connected to the flight body;

a controller to control operation the autogyro assembly for unmanned flight; and

a sensor to detect other objects adjacent the air vehicle.

15. The system of claim 14, wherein the air vehicle is adapted to provide electronic protection to the towing vehicle.

16. The system of claim 14, wherein the sensor increases a sensor range by at least three times relative to a horizon detection distance.

17. The system of claim 16, wherein the towing vehicle is a water craft.

18. The system of claim 17, wherein the water craft includes a winch including a line windable thereon and connected to the air vehicle.

19. The system of claim 17, wherein the controller operates the winch.

20. The system of claim 16, wherein the flight body includes a connection to connect to a powered land vehicle or water craft to provide forward motive force to power the autogyro assembly.

21. The system of claim 20, 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.

22. The system of claim 20, 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 air vehicle through takeoff absent a further motive force.

23. The system of claim 22, wherein the controller is to sense forward motion to control the autogyro assembly.

24. The system of claim 23, wherein the controller is to receive signal from a propulsion device and to control the autogyro assembly using the received signal.

25. The system of claim 23, wherein the controller is to control the rotational speed of the hub.

26. The system of claim 23, wherein the autogyro assembly comprises actuators to control angle of the plurality of airfoil blades, and wherein the controller controls the actuators.

27. The system of claim 26, wherein the controller is to issue control signals to position airfoil blades for different stages of flight.

28. The system of claim 26, wherein the controller is to issue a flight control signal to set the airfoil blades for flight.

29. The system of claim 14, 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.