Towable autogyro having a re-positionable mast

• US 9,187,173 B2
• Filed: 01/02/2014
• Issued: 11/17/2015
• 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.
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Fabula, Michael A
• Application Number:
  US14/146,505
• Publication Number:
  US 20140246538A1
• Time in Patent Office: 684 Days
• Field of Search: 244/1.TD, 244/8, 244/17.11, 244/17.13, 244/17.17, 244/17.23, 244/17.27, 244/189, 244/118.1, 244/118.2, 244/154, 244/153.A
• US Class Current: 1/1
• 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 10/11 Autogyros
• CPC Class Codes: B64U 2101/64 for parcel delivery or retrieval
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: B64U 30/291 Detachable rotors or rotor supports
• CPC Class Codes: B64U 50/19 using electrically powered motors
• CPC Class Codes: B64U 80/82 Airborne vehicles
• CPC Class Codes: B64U 80/84 Waterborne 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 towed in flight by a towing vehicle, comprising:

an unmanned flight body;

a plurality of weight sensors configured to sense weight of the air vehicle;

an autogyro assembly connected to the flight body;

an electric motor-generator connected to provide mechanical power to the autogyro assembly in a motor mode and convert power from the autogyro assembly to electrical power in a generator mode;

an actuator connected to the autogyro assembly that is actuated to move the location of the autogyro assembly relative to the flight body; and

a controller programmed to control operation the autogyro assembly for unmanned flight, wherein the controller receives weight data provided the plurality of weight sensors, calculates a center of gravity associated with the towed air vehicle in response to the received weight data, and in response to the calculated center of gravity controls the actuator to change the location of the autogyro assembly in response to the received weight data.

2. The air vehicle of claim 1, further including a sensor programmed to detect other objects adjacent the air vehicle, wherein the sensor receives electric power from the generator.

3. 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.

4. The vehicle of claim 3, wherein the controller is programmed to sense forward motion of the air vehicle to control the autogyro assembly.

5. The vehicle of claim 4, wherein the controller is programmed to receive a signal from a propulsion device and programmed to control the autogyro assembly using the received signal.

6. The vehicle of claim 5, wherein the controller is programmed to control the rotational speed of the hub, wherein the autogyro assembly comprises additional actuators to control angle of the plurality of airfoil blades, and wherein the controller is programmed to control the additional actuators, and wherein the flight body comprises a container to house the controller, a flight stabilizer, and an undercarriage to support the container when on the ground.

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

8. An air vehicle towed in flight by a marine vessel, the air vehicle comprising:

a flight body;

a plurality of legs extending from the flight body to support the towed air vehicle when on the ground;

a weight sensor attached to each of the plurality of legs for sensing weight loaded on each of the plurality of legs;

an autogyro assembly connected to the flight body;

wherein the autogyro assembly comprises;

a mast,

a rotatable hub on an end of the mast, and

a plurality of blades connected to the hub;

an electric motor-generator connected to selectively provide motive force to the rotatable hub in a motor mode and generate electrical power from the rotatable hub in the generator mode;

at least one actuator connected to the autogyro assembly to change the location of the autogyro assembly relative to the flight body;

a controller programmed to control operation of the autogyro assembly for unmanned flight, wherein the controller receives weight data provided the plurality of weight sensors, calculates a center of gravity associated with the towed air vehicle in response to the received weight data, and in response to the calculated center of gravity is programmed to control the actuator to change the location of the autogyro assembly in response to the received weight data.

9. The air vehicle of claim 8, wherein the at least one actuator is capable of moving the mast forward, aft, left, and right.

10. The air vehicle of claim 8, wherein the flight body includes a connection to connect to the marine vehicle to provide forward motive force to power the autogyro assembly.

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

12. The air vehicle of claim 11, wherein the controller is programmed to receive a signal from a propulsion device and is programmed to control the autogyro assembly using the received signal.

13. The air vehicle of claim 11, wherein the controller is programmed to control the rotational speed of the hub.

14. The air vehicle of claim 11, wherein the autogyro assembly comprises additional actuators to control angle of the plurality of airfoil blades, and wherein the controller is programmed to control the additional actuators.

15. The air vehicle of claim 14, wherein the controller is programmed to issue control signals to the additional actuators to position the airfoil blades for different stages of flight.

16. The air vehicle of claim 8, wherein the controller is programmed to generate an error message if the location of the autogyro cannot be located at the calculated center of gravity.