A plug-in assembly structure for a UAV includes a first component (1), a second component (2) and a limit assembly (3). The first component (1) includes a first plug (11) and a positioning sleeve (12), and the positioning sleeve (12) is provided with a first through hole (121). The second component (2) includes a second plug (21), the radial direction of the second plug (21) is provided with a limit hole (2111), the second plug (21) can be electrically connected to the first plug (11), and the limit hole (2111) is facing the first through hole (121). The limit assembly (3) is installed in the limit hole (2111). The limit assembly (3) includes a first elastic element (31) and a limit element (32).

In various embodiments, specialized vehicle launch systems and methods are provided to enable personnel to launch and operate one or more UAVs from the safety of a vehicle or other mobile location. In various embodiments, a launch system comprises a launch device and an operator terminal. The launch device is adapted to be mounted on an exterior surface of a vehicle and is communicably coupled to the operator terminal, which is operable from the interior of the vehicle. The vehicle launch system allows an operator to control one or more UAVs from inside the vehicle, without requiring the operator to step outside of the vehicle to interact with the UAV or launch device. The UAVs include foldable articulating arms facilitating storage in cylindrical launch/land unit housings. Each UAV is stored on a landing platform comprising an extended landing platform that include articulating arms and foldable surface.

In various embodiments, specialized vehicle launch systems and methods are provided to enable personnel to launch and operate one or more UAVs from the safety of a vehicle or other mobile location. In various embodiments, a launch system comprises a launch device and an operator terminal. The launch device is adapted to be mounted on an exterior surface of a vehicle and is communicably coupled to the operator terminal, which is operable from the interior of the vehicle. The vehicle launch system allows an operator to control one or more UAVs from inside the vehicle, without requiring the operator to step outside of the vehicle to interact with the UAV or launch device. The UAVs include foldable articulating arms facilitating storage in cylindrical launch/land unit housings. Each UAV is stored on a landing platform comprising an extended landing platform that include articulating arms and foldable surface.

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.

Embodiments are directed to a rotorcraft comprising a body having a longitudinal axis, a wing coupled to the body, a single tiltrotor assembly pivotally coupled to the body, and the tiltrotor assembly configured to move between a position generally perpendicular to the longitudinal axis during a vertical flight mode and a position generally parallel to the longitudinal axis during a horizontal flight mode. The rotorcraft may further comprise an anti-torque system configured to counteract torque generated by the tiltrotor assembly during vertical flight. The rotorcraft may further comprise a center of gravity compensation system configured to manage a rotorcraft center of gravity during movement of the tiltrotor assembly between the vertical flight mode and the horizontal flight mode.

An aerial vehicle with a plurality of selectively collapsible arms capable of transitioning between an extended state and a contracted state is described. In the extended position, the distance between the main body of the vehicle and the rotor associated with each arm is maximized. In the contracted state, the distance between the main body of the vehicle and the rotor associated with each arm is minimized. In certain embodiments, each of the arms may include one or more tape springs that are biased to selectively move the associated one or more rotors of each arm between the retracted and extended states.

A modular flat-packable drone kit includes a plurality of components that can be assembled into a drone. Components of the drone kit include elements that may be cut from a flat sheet of material, thereby enabling low cost manufacturing and compact packaging and may be assembled without specialized tools. A set of drones may operate in a standalone mode or may be coupled together and operated in a group configuration.

A modular flat-packable drone kit includes a plurality of components that can be assembled into a drone. Components of the drone kit include elements that may be cut from a flat sheet of material, thereby enabling low cost manufacturing and compact packaging and may be assembled without specialized tools. A set of drones may operate in a standalone mode or may be coupled together and operated in a group configuration.

A reconfigurable hybrid Vertical Takeoff and Landing (VTOL) vehicle includes a turntable bearing coupling a conventional wing to a fuselage. The fuselage, designed to couple to and release a cargo pod from its undercarriage, is configured to accept a high wing juncture such that the wing can rotate from a flight configuration to a transport configuration. The transport configuration aligns the wing with the fuselage sufficient to enable the hybrid VTOL vehicle to fit within a standard intermodal container or transport aircraft.

A reconfigurable hybrid Vertical Takeoff and Landing (VTOL) vehicle includes a turntable bearing coupling a conventional wing to a fuselage. The fuselage, designed to couple to and release a cargo pod from its undercarriage, is configured to accept a high wing juncture such that the wing can rotate from a flight configuration to a transport configuration. The transport configuration aligns the wing with the fuselage sufficient to enable the hybrid VTOL vehicle to fit within a standard intermodal container or transport aircraft.