In-flight reconfigurable hybrid unmanned aerial vehicle
First Claim
1. An unmanned aerial vehicle (UAV) comprising:
- a fuselage configured to support transport of cargo that is coupled to the fuselage or stored within the fuselage;
a plurality of propulsion units coupled directly or indirectly to the fuselage;
a main wing coupled to the fuselage;
a tail rotatably coupled to the fuselage, wherein the tail extends outward from the fuselage and along a longitudinal axis of the fuselage, wherein the tail is configured to rotate about a pivot between a first position and a second position, wherein the first position corresponds to an extended position used during horizontal flight and the second position corresponds to a stowed position used during vertical flight, and wherein the tail is in a substantially horizontal inward orientation in the second position;
a drive mechanism coupled to or stored within the fuselage, wherein the drive mechanism is configured to cause the tail to rotate about the pivot between the first position and the second position;
a power source coupled to or stored within the fuselage, wherein the power source is configured to provide power to at least the plurality of propulsion units and the drive mechanism; and
a control system coupled to or stored within the fuselage, wherein the control system is in communication with at least the plurality of propulsion units and the drive mechanism, and wherein the control system is configured to control at least operation of the plurality of propulsion units and operation of the drive mechanism.
1 Assignment
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Accused Products
Abstract
This disclosure is directed to an unmanned aerial vehicle (“UAV”) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a fuselage or wing. The UAV may include a tail and/or a swing arm that is rotatably coupled to the fuselage and that rotate between different positions. The swing arm may be selectively coupled to cargo. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon.
34 Citations
13 Claims
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1. An unmanned aerial vehicle (UAV) comprising:
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a fuselage configured to support transport of cargo that is coupled to the fuselage or stored within the fuselage; a plurality of propulsion units coupled directly or indirectly to the fuselage; a main wing coupled to the fuselage; a tail rotatably coupled to the fuselage, wherein the tail extends outward from the fuselage and along a longitudinal axis of the fuselage, wherein the tail is configured to rotate about a pivot between a first position and a second position, wherein the first position corresponds to an extended position used during horizontal flight and the second position corresponds to a stowed position used during vertical flight, and wherein the tail is in a substantially horizontal inward orientation in the second position; a drive mechanism coupled to or stored within the fuselage, wherein the drive mechanism is configured to cause the tail to rotate about the pivot between the first position and the second position; a power source coupled to or stored within the fuselage, wherein the power source is configured to provide power to at least the plurality of propulsion units and the drive mechanism; and a control system coupled to or stored within the fuselage, wherein the control system is in communication with at least the plurality of propulsion units and the drive mechanism, and wherein the control system is configured to control at least operation of the plurality of propulsion units and operation of the drive mechanism. - View Dependent Claims (2, 3, 4, 5)
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6. An aerial vehicle comprising:
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a fuselage; a plurality of propulsion units coupled to the fuselage; a tail rotatably coupled to the fuselage, the tail extending outward from the fuselage and including control surfaces for use during horizontal flight, the tail configured to rotate about a tail pivot to transition the tail between a first position and a second position, wherein the first position is an extended position used in a horizontal flight configuration and the second position is a stowed position used in a vertical flight configuration, and wherein the tail is in a substantially horizontal inward orientation in the second position; and a drive mechanism coupled to the fuselage, wherein the drive mechanism is configured to selectively rotate the tail about the tail pivot. - View Dependent Claims (7, 8, 9, 10, 11, 12, 13)
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Specification