An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, a line having one end coupled to the chassis and an opposite free end, wherein the free end is positioned below the chassis, and a severing mechanism operable to sever the line under control of the control system.

An example charging station for an unmanned aerial vehicle (UAV), the charging station generally including a nest and a charging device. The nest includes an upper portion and a lower portion. The upper portion defines an upper opening sized and shaped to receive a landing apparatus of the UAV, and a diameter of the nest reduces from a first diameter at the upper opening to a second diameter at the lower portion. The charging device is mounted in the nest, and includes a first contact pad and a second contact pad. The charging device is configured to apply a voltage differential across the first contact pad and the second contact pad such that the charging station is operable to charge a power supply of the UAV via the landing apparatus.

An example charging station for an unmanned aerial vehicle (UAV), the charging station generally including a nest and a charging device. The nest includes an upper portion and a lower portion. The upper portion defines an upper opening sized and shaped to receive a landing apparatus of the UAV, and a diameter of the nest reduces from a first diameter at the upper opening to a second diameter at the lower portion. The charging device is mounted in the nest, and includes a first contact pad and a second contact pad. The charging device is configured to apply a voltage differential across the first contact pad and the second contact pad such that the charging station is operable to charge a power supply of the UAV via the landing apparatus.

A multi-rotor unmanned aerial vehicle (UAV) includes a central body including an outer surface and an inner surface, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, one or more receiving structures positioned on the outer surface of the central body and configured to receive one or more electrical components, the one or more electrical components comprising at least a battery of the UAV, and an indicator light disposed at an opening or a window on one of the plurality of branch members, wherein the opening or the window is made of a transparent or semi-transparent material.

A multi-rotor unmanned aerial vehicle (UAV) includes a central body including an outer surface and an inner surface, a plurality of branch members connected to the central body, each branch member configured to support a corresponding actuator assembly, one or more receiving structures positioned on the outer surface of the central body and configured to receive one or more electrical components, the one or more electrical components comprising at least a battery of the UAV, and an indicator light disposed at an opening or a window on one of the plurality of branch members, wherein the opening or the window is made of a transparent or semi-transparent material.

A wing (3) for an aircraft (1) including a fixed wing (5), a foldable wing tip portion (9) mounted to the fixed wing (5) via a first hinge (11) rotatable about a first hinge axis (13) between an extended position (15) and a folded position (17), and an actuation unit (19) arranged at the fixed wing (5) and coupled to the foldable wing tip portion (9) via a linkage (21) including a first link element (23) and a second link element (25), wherein the first link element (23) is mounted to a rotatable output (27) of the actuation unit (19) and is rotatably coupled to the second link element (25) via a second hinge (29), and wherein the second link element (25) is rotatably coupled to the foldable wing tip portion (9) via a third hinge (31).

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.

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.

Adaptive wing systems and aircraft. A variable-span wing for aircraft comprises a fixed-section (1) with skin (118) that forms a lift-generating wing surface, and further comprises a top and a bottom moveable section (2) that are vertically offset from one-another and which translate in substantially lateral directions into and out of the fixed-section (1) through fixed-section tip-openings (126). The moveable sections (2) overlap inside of the fixed-section (1) when fully retracted. The wing also comprises at least two tracks (310,316) and track-mating parts (320). The track-mating parts (320) are attached near the roots of the moveable sections (2) and translate along the tracks (310,316) to guide the moveable sections (2). A non-overlapped wing with motors (331) that translate with the moveable sections (2) and which have attached gear heads (332). A rack (341) is located within the fixed section (1). Rotation of the gear heads (332) against the rack (341) causes the moveable sections (2) to translate. A non-overlapped wing having two disc-like elements (334) and a loop-like element (343) around the disc-like elements (334). Rotation of a disc-like element (334) causes the loop-like element (343) to push-and-pull the moveable sections (2) in opposing directions into and out of the fixed section (1). An aircraft utilizing the first-described wing having a propulsion system (8) and a set of elevons (5).

A method according to certain embodiments generally involves operating a system including an unmanned aerial vehicle (UAV) and a base station. The base station includes a nest including an upper opening having an upper opening diameter and a lower opening having a lower opening diameter less than the upper opening diameter. The lower opening is accessible from within the base station. The method generally includes landing the UAV within the nest such that a portion of the UAV is accessible via the lower opening, releasably attaching a load to the UAV, and operating the UAV to deliver the load to a destination.