The embodiment is an unmanned aerial vehicle, including a body and wings. A first connection portion is disposed on one of the body and the wing. A second connection portion is disposed on the other of the body and the wing. The first connection portion and the second connection portion are detachably connected. The first connection portion is engaged with the second connection portion. The body and the wing are locked by rotating or sliding the second connection portion. The body can be conveniently assembled with or disassembled from the wing and the connection part meets the reliability of strength and rigidity and does not affect the flight performance.

A modular unmanned aerial system includes a chassis for attaching components of the modular unmanned aerial system and one or more rotary wings. Each of the one or more rotary wings is drivable by a respective motor. A central controller is provided for controlling operation of the modular unmanned aerial system. A modular interface portion attached to the chassis and adapted for removably mounting one or more modular devices.

An aircraft has an empennage and a folding system. The folding system has aerofoils and node bodies which are connected to one another. The aerofoils have at least two nose-side aerofoils and at least two tail-side aerofoils, of which one of the nose-side aerofoils and one of the tail-side aerofoils are port-side aerofoils and one of the nose-side aerofoils and one of the tail-side aerofoils are starboard-side aerofoils. The node bodies have fuselage-side node bodies and outer node bodies. The nose-side aerofoils and tail-side aerofoils are each articulated at a first end to an associated fuselage-side node body, and the nose-side aerofoils and tail-side aerofoils are each articulated at a second end to an outer node body. The tail-side node bodies are displaceable at least partially along an associated translation axis. The folding system functions as the empennage during flight.

A vertical takeoff and landing unmanned aerial vehicle and a cooling system for the unmanned aerial vehicle. Heat dissipation in an arm of an unmanned aerial vehicle is achieved by providing a forward-facing opening at the front end of each of a left linear support and a right linear support of the unmanned aerial vehicle, thereby achieving the purposes of lowering temperature in the arm and protecting equipment in the arm.

An apparatus including a display, an antenna, and processing circuitry that receives, via the antenna, a near-field communication data packet from an antenna of a secondary device, the near-field communication data packet including information regarding a functional type of the secondary device, and updates graphics of the display based on the functional type of the secondary device.

A multicopter system according to one aspect of the present invention includes a multicopter configured to fly in a state of holding a package and a mooring device that is installed at a target position of a flight of the multicopter and includes a linear member that extends in a predetermined direction from the target position, the multicopter including a reception portion that has the shape of a recess including an opening open toward one direction and is configured to receive the linear member via the opening.

Disclosed are apparatus, systems, and methods, including a ground transport drive container comprising an outer container having a cuboid shape and comprising a plurality of fittings for securing the outer container to another apparatus; and a drive wheel assembly. The drive wheel assembly comprises one or more wheels and a deployment mechanism secured to the one or more wheels. An actuating member actuates the drive wheel assembly between a stowed configuration and one or more deployed configurations. In the stowed configuration, the drive wheel assembly is housed entirely within the outer container. In the one or more deployed configurations, the drive wheel assembly extends from the outer container.

A configurable unmanned aerial vehicle (UAV) may include swappable components that may be selectable to configure a customized UAV just prior to deployment of the UAV that is configured to deliver a package to a destination. The UAV may include a plurality of ports that may accept swappable components. The ports may be coupled to a logic board to enable control of the swappable components. The ports and swappable components may enable quick replacement of a malfunctioning components, such as an image sensor, which may avoid subjecting a UAV to significant downtime for service. The malfunctioning component may then be serviced after the UAV is readied for a subsequent flight or deployed on a subsequent flight.

An aerostructure assembly of an aircraft is disclosed having a first aerostructure portion extending in a direction between a first position and a second position and including structurally of at least one rib or spar portion at least partially enclosed by a cover portion; a corresponding second aerostructure portion connected to the first aerostructure portion and extending continuously in the direction from the first aerostructure portion between the second position and a third position and including structurally of at least one further rib or further spar portion at least partially enclosed by a further cover portion. The first aerostructure portion has a first aerodynamic planform area (SI) and the corresponding second aerostructure portion has a corresponding second aerodynamic planform area (S2). A total aerodynamic planform area of the first aerostructure portion and corresponding second aerostructure portion is equal to the sum of the first aerodynamic planform area and the corresponding second aerodynamic planform area.

A propulsion module of an air mobility vehicle may include a door provided in the housing and opening or closing the opening portion of the housing by a sliding motion of the door; a propeller for providing propulsion to the air mobility vehicle; a link assembly having a first end portion connected to the housing and a second end portion connected to the propeller to pull the propeller into the internal space of the housing through the opening portion or pull the propeller outside the internal space through the opening portion; and a door opening and closing portion coupled to the door and configured for providing an opening and closing force to the door according to an inward-pulling motion or an outward-pulling motion of the propeller.