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 win
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 wing. 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. In this vertical flight configuration, the UAV may perform vertical flight or hover. During the vertical flight, the UAV may cause the wing to extend outward via the pivots such that the wing segments become positioned substantially parallel to one another and the wing resembles a conventional fixed wing. With the wing extended, the UAV assumes a horizontal flight configuration that provides upward lift generated from the wing.
대표청구항▼
1. An unmanned aerial vehicle (UAV) comprising: a fuselage configured to transport cargo that is coupled to the fuselage or stored within the fuselage;a plurality of propulsion units to cause propulsion of the UAV;a main wing coupled to the fuselage, the main wing having a plurality of wing segments
1. An unmanned aerial vehicle (UAV) comprising: a fuselage configured to transport cargo that is coupled to the fuselage or stored within the fuselage;a plurality of propulsion units to cause propulsion of the UAV;a main wing coupled to the fuselage, the main wing having a plurality of wing segments, each wing segment spanning between two different ones of the plurality of propulsion units, the main wing including: coupling features to couple each of the plurality of propulsion units;a plurality of pivots, each pivot located between adjacent wing segments, the plurality of pivots configured to modify a shape of the wing between (i) a horizontal flight configuration where the plurality of wing segments are oriented approximately parallel to one another and (ii) a vertical flight configuration where the plurality of wing segments symmetrically orient the plurality of propulsion units around the fuselage; anda drive mechanism to cause the plurality wing segments to rotate about the plurality of pivots during flight to transition between the horizontal flight configuration and the vertical flight configuration;a power source coupled to the fuselage to selectively provide power to the plurality propulsion units and the drive mechanism; anda control system coupled to the fuselage and in communication with at least the plurality of propulsion units, the drive mechanism, and the power source, the control system to control at least operation of the plurality of propulsion units and a transition of the main wing between the horizontal flight configuration and the vertical flight configuration,wherein the UAV is configured to (i) sustain horizontal flight in the horizontal flight configuration while the fuselage is oriented parallel to a horizon and (ii) sustain vertical flight in the vertical flight configuration while the fuselage is oriented perpendicular with the horizon. 2. The UAV as recited in claim 1, further comprising a tail that extends outward from the fuselage and includes control surfaces for use during the horizontal flight in the horizontal flight configuration, the tail configured to rotate about a pivot to transition the tail from an extended position used in the horizontal flight configuration to a stowed position during vertical flight in the vertical flight configuration. 3. The UAV as recited in claim 1, wherein the main wing is a swept wing that includes control surfaces on a trailing edge that extends behind an aft end of the fuselage. 4. The UAV as recited in claim 1, further comprising: at least two wing support arms that couple to respective coupling features located on the main wing when the UAV is in the vertical flight configuration, each wing support arm to stabilize a wing segment when coupled to a respective coupling feature; anda stiffening cable assembly coupled to the wing assembly, the stiffening cable assembly configured to stiffen the wing assembly in the horizontal flight configuration when the stiffening cable assembly is in tension. 5. An aerial vehicle comprising: a fuselage;a plurality of propulsion units; anda wing assembly comprising a plurality of wing segments, wherein each of the plurality of wing segments is connected to an adjacent wing segment through a respective pivot,wherein each pivot defines a pivot axis between an intersection of the respective pivot with a leading edge and a trailing edge of the wing assembly,wherein the plurality of wing segments are configured to rotate around the pivot axis during flight between (i) a horizontal flight configuration where the plurality of wing segments are oriented approximately parallel to one another and (ii) a vertical flight configuration where the plurality of wing segments are positioned around the fuselage,wherein one of the plurality of propulsion units is located proximate to and substantially parallel with each pivot axis. 6. The aerial vehicle as recited in claim 5, further comprising a swing arm rotatably coupled to the fuselage, the swing arm to selectively couple to cargo, the swing arm to position the cargo in a first position under the fuselage when the aerial vehicle is in the vertical flight configuration and in a second, different position under the fuselage when the aerial vehicle is in the horizontal flight configuration. 7. The aerial vehicle as recited in claim 5, further comprising a tail that extends outward from the fuselage and includes control surfaces for use during horizontal flight in the horizontal flight configuration, the tail configured to rotate about a tail pivot to transition the tail from an extended position used in the horizontal flight configuration to a stowed position used in the vertical flight configuration. 8. The aerial vehicle as recited in claim 5, wherein a fore end of the fuselage further comprises at least one imaging sensor used to assist in navigation of the aerial vehicle. 9. The aerial vehicle as recited in claim 5, wherein the wing assembly comprises three wing segments and two pivots. 10. The aerial vehicle as recited in claim 5, wherein one of the plurality of propulsion units is located proximate to opposite ends of each wing segment. 11. The aerial vehicle as recited in claim 5, wherein the wing assembly further comprises locking arms to stiffen the wing assembly in the horizontal flight configuration. 12. The aerial vehicle as recited in claim 5, wherein at least one of the wings segments comprises a swept-wing shape. 13. The aerial vehicle as recited in claim 5, further comprising at least two wing support arms that couple to respective coupling features located on the wing assembly when the aerial vehicle is in the vertical flight configuration, each support arm of the at least two wing support arms to stabilize a wing segment when coupled to a respective coupling feature. 14. The aerial vehicle as recited in claim 5, further comprising a drive mechanism configured to rotate the plurality of wing segments about each pivot. 15. The aerial vehicle as recited in claim 5, wherein the drive mechanism comprises at least one of a servo, a linear actuator, and an electric motor. 16. An aerial vehicle comprising: a plurality of propulsion units;a wing assembly having a plurality of wing segments coupled to at least one propulsion unit of the plurality of propulsion units and coupled to at least one of a plurality of pivots, each wing segment spanning between two different ones of the plurality of propulsion units, each wing segment rotatably coupled to at least one other wing segment by a pivot of the plurality of pivots that are configured to modify a shape of the wing assembly during flight between (i) a horizontal flight configuration where the plurality of wing segments are oriented approximately parallel to one another and (ii) a vertical flight configuration where the plurality of wing segments position the plurality of propulsion units to form a substantially symmetrical parallelogram; anda drive mechanism to cause the plurality of wing segments to rotate about the plurality of pivots to transition the shape of the wing assembly between the horizontal flight configuration and the vertical flight configuration. 17. The aerial vehicle as recited in claim 16, wherein the aerial vehicle is configured to (i) sustain horizontal flight in the horizontal flight configuration while the wing assembly is oriented parallel to a horizon and (ii) sustain vertical flight in the vertical flight configuration while the wing assembly is oriented perpendicular with the horizon. 18. The aerial vehicle as recited in claim 16, wherein at least one of the plurality of wing segments comprises a swept-wing shape. 19. The aerial vehicle as recited in claim 16, wherein the plurality of pivots are located at locations on the wing assembly that are different than locations of the plurality of propulsion units. 20. The aerial vehicle as recited in claim 16, wherein the propulsion units are rotor units, each rotor unit including an electric motor to rotate at least one rotor to generate thrust to cause propulsion of the UAV, and wherein the at least one rotor is configured for variable pitch, the variable pitch configured to reverse a direction of the thrust.
연구과제 타임라인
LOADING...
LOADING...
LOADING...
LOADING...
LOADING...
이 특허에 인용된 특허 (6)
Moore, Michael, Insect-like micro air vehicle having perching, energy scavenging, crawling, and offensive payload capabilities.
※ AI-Helper는 부적절한 답변을 할 수 있습니다.