초록 ▼

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

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.

대표청구항 ▼

1. An aerovehicle system, comprising: a towing aircraft;a towed aerovehicle; anda tow line releasably connected between the towing aircraft and towed aerovehicle, the towed aerovehicle including; a flight body;an autogyro assembly connected to the flight body; anda controller to control operation of

1. An aerovehicle system, comprising: a towing aircraft;a towed aerovehicle; anda tow line releasably connected between the towing aircraft and towed aerovehicle, the towed aerovehicle including; a flight body;an autogyro assembly connected to the flight body; anda controller to control operation of the autogyro assembly for unmanned flight;wherein, when the controller determines a stall in the towing aircraft, the controller automatically releases the tow line and controls the flight of the towed aerovehicle to a landing by substantially following a flight path determined by sensed signals and a programmed destination. 2. The aerovehicle system 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. 3. The aerovehicle system of claim 2, 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. 4. The aerovehicle system of claim 3, wherein the controller senses forward motion in order to control the autogyro assembly. 5. The aerovehicle system of claim 4, wherein the controller receives signals from the towing aircraft and controls the autogyro assembly using the received signals. 6. The aerovehicle system of claim 5, wherein the controller controls the rotational speed of the hub. 7. The aerovehicle system of claim 2, wherein the autogyro assembly comprises actuators which control angle of the plurality of airfoil blades, and wherein the controller controls the actuators. 8. The aerovehicle system of claim 1, wherein the flight body comprises a container to hold cargo, a rear stabilizer, and an undercarriage which supports the container when on the ground. 9. The aerovehicle system of claim 8, wherein the undercarriage includes a trolley that contacts the ground to provide mobility and is removable from the container. 10. The aerovehicle system of claim 1, wherein the controller issues control signals to position the airfoil blades for different stages of flight. 11. The aerovehicle system of claim 10, wherein the controller issues a flight control signal to set the airfoil blades for flight. 12. The aerovehicle system of claim 11, wherein the controller issues a take-off 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. 13. The aerovehicle system of claim 12, wherein the controller issues 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. 14. The aerovehicle system of claim 13, wherein the controller issues a landing control signal to set the airfoil blades for landing, wherein the angle of incidence of the airfoil blades is greatest at landing. 15. The aerovehicle system of claim 14, 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. 16. The aerovehicle system of claim 1, wherein the controller controls a propulsion system that has sufficient thrust to assist in a cargo laden flight and an essentially cargo-free flight but does not have enough thrust to fly a flight body full of cargo. 17. The aerovehicle system of claim 16, 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. 18. The aerovehicle system of claim 1, wherein the tow line includes a mechanical component to transfer trust from the towing aircraft to the flight body and an electrical component that transfers electrical signals from the towing aircraft to the controller. 19. The aerovehicle system of claim 1, wherein the controller receives signals from other controllers of nearby aerovehicles. 20. The aerovehicle system of claim 19, wherein the controller acts as a master controller and issues control signals to nearby aerovehicles. 21. The aerovehicle system of claim 1, wherein a plurality of aerovehicles are towed by the towing aircraft simultaneously. 22. The aerovehicle system 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. 23. The aerovehicle system of claim 22, wherein the sensors include weight sensors on the 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. 24. The aerovehicle system of claim 23, 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. 25. The aerovehicle system of claim 1, wherein the controller receives a forward air speed indicator to control the speed of the flight body and keeps the speed below a never-exceed velocity. 26. The aerovehicle system of claim 1, wherein the controller receives a rotation speed signal from the autogyro assembly and issues a brake signal if the rotational speed exceeds a safe rotational speed. 27. The aerovehicle system of claim 1, further comprising a propulsion system and wherein the controller controls operation of the propulsion system.