IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0410225
(2012-03-01)
|
등록번호 |
US-9033281
(2015-05-19)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
8 인용 특허 :
1 |
초록
▼
A radio controlled UAV is disclosed. The UAV includes a parachute, with a cylindrical power and control module suspended vertically below the parachute. In one embodiment, a propulsion source is mounted on top of the power and control module with control lines connected to the module below the propu
A radio controlled UAV is disclosed. The UAV includes a parachute, with a cylindrical power and control module suspended vertically below the parachute. In one embodiment, a propulsion source is mounted on top of the power and control module with control lines connected to the module below the propulsion source, and in another embodiment the power and control module is suspended from a point above a propulsion source. The UAV is controlled by radio controls from a hand held controller, with actuators retracting and letting out control lines attached to the parachute in order to control direction of the parachute. The UAV may be launched from a tube using a pressurized tank with a nozzle expelling gas from the tank, the tank and nozzle towing a canister from which the UAV is deployed.
대표청구항
▼
1. An unmanned aerial reconnaissance vehicle (UAV) system comprising: a parachute having a plurality of control lines comprising at least one first control line attached to one portion of said parachute and at least one second control line attached to another portion of said parachute, said parachut
1. An unmanned aerial reconnaissance vehicle (UAV) system comprising: a parachute having a plurality of control lines comprising at least one first control line attached to one portion of said parachute and at least one second control line attached to another portion of said parachute, said parachute configured to be steered by simultaneous vertical movement of said at least one first control line and said at least one second control line,a power and control module of an elongated, generally cylindrical configuration suspended in a vertical orientation below said parachute, said power and control module further comprising: a propulsion device mounted at an upper portion of said power and control module, enabling said UAV to gain altitude, maintain altitude and to horizontally reposition said UAV following launch of said UAV,a signal receiver in said power and control module,a control mechanism attached to said at least one first control line and said at least one second control line, said control mechanism responsive to signals received by said signal receiver to move said at least one first control line and said at least one second control line in said simultaneous vertical movement, for controlling direction of said parachute, anda remote controller that transmits said signals to a flying said UAV. 2. A UAV system as set forth in claim 1 wherein said power and control module is suspended in said vertical orientation by said at least one first control line and said at least one second control line, said first control line and said second control line coupled to said upper portion of said power and control module. 3. A UAV system as set forth in claim 1 wherein said at least one first control line and said at least one second control line are attached to said control mechanism, said control mechanism located below said propulsion device. 4. A UAV system as set forth in claim 3 wherein said propulsion device is a ducted fan driven by a motor. 5. A UAV system as set forth in claim 2 wherein said control mechanism is at said upper portion of said power and control module, with said at least one first control line and said at least one second control line attached to said control mechanism at said upper portion of said power and control module. 6. A UAV system as set forth in claim 4 wherein said ducted fan is mounted for pivoting about a horizontal axis, with an actuator responsive to said signals received by said signal receiver, said actuator connected to controllably pivot said ducted fan in vertical directions, thereby controlling altitude of said UAV. 7. A UAV system as set forth in claim 5 wherein said control mechanism further comprises a single control element operated by said control mechanism, said at least one first control line and said at least one second control line attached to said single control element, said single control element operable by said control mechanism to move said at least one first control line and said at least one second control line in said simultaneous vertical movement. 8. A UAV system as set forth in claim 7 wherein said control mechanism moves said at least one first control line and said at least one second control line simultaneously in opposite said vertical directions with respect to each other. 9. A UAV system as set forth in claim 8 wherein said at least one first control line is attached to said single control element on one side of said upper portion, and said at least one second control line is attached to said single control element on an opposite side of said upper portion. 10. A UAV system as set forth in claim 9 wherein said single control element further comprises a first end on said one side of said power and control module and a second end on said opposite side of said power and control module, with said first control line attached to said first end of said single control element and said second control line attached to said second end of said single control element. 11. A UAV system as set forth in claim 10 wherein said single control element is a shaft rotated by said control mechanism, with a first pulley attached to said first end at said one side of said upper portion and a second pulley attached to said second end at said opposite side of said upper portion, with said first control line wound in one direction around said first pulley and said second control line wound in an opposite direction around said second pulley, so that rotation of said shaft develops said simultaneous vertical movement of said at least one first control line and said at least one second control line in said opposite vertical directions with respect to each other, thereby controllably steering said parachute. 12. An unmanned aerial reconnaissance vehicle (UAV) system comprising: a parachute,a first control line attached to one portion of said parachute and a second control line attached to another portion of said parachute, said parachute steered by simultaneous vertical movement of said first control line and said second control line,an elongated, generally cylindrical power and control module suspended in a vertical orientation below said parachute, said power and control module further comprising: a propulsion device mounted at an upper portion of said control module enabling said UAV to gain altitude, maintain altitude and to horizontally reposition said UAV following launch of said UAV,a signal receiver,a single control mechanism in said upper portion of said power and control module, and responsive to signals from said signal receiver, said single control mechanism attached to said first control line and said second control line, for moving said first control line and said second control line control lines in said simultaneous vertical movement, anda remote controller that transmits said signals to a flying said UAV. 13. A UAV system as set forth in claim 12 wherein said single control mechanism operates to move said first control line and said second control line simultaneously in opposite vertical directions with respect to each other. 14. A UAV system as set forth in claim 13 wherein said first control line is attached to said single control mechanism on one side of said upper portion, and said second control line is attached to said single control mechanism on an opposite side of said upper portion. 15. A UAV system as set forth in claim 14 wherein said propulsion device is mounted at said upper portion of said power and control module. 16. A UAV system as set forth in claim 15 further comprising a camera mounted at a lower end of said power and control module. 17. A UAV system as set forth in claim 16 wherein said propulsion device further comprises a powered airfoil. 18. A UAV system as set forth in claim 17 wherein power applied to said powered airfoil determines altitude of said UAV. 19. A UV system as set forth in claim 12 wherein a ratio between a surface area of said parachute and weight of said power and control module is approximately 36 square inches of parachute for each ounce of said control module.
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