A drone propeller of the present invention includes a plurality of blades and a rotary shaft, wherein the blades comprise a rotation retaining unit connected to the rotary shaft side, a separation and detachment unit that is on the outer side of the blades and is to be separated when damaged, and a breakage inducing unit which connects the rotation retaining unit and the separation and detachment unit and is damaged during a collision.

A rotary aircraft includes a cover, a driving shaft in the cover, an electric control board on the cover, and a flight assembly mounted on the driving shaft and coupled electrically with the electrical control board, a driving assemble mounted on the flight assembly and coupled electrically with the electrical control board, connected with the driving shaft and driving it to rotate so as to rotate the cover, and a light bar mounted on the cover and coupled electrically with the electrical control board, used for displaying a presetting pattern or text, which achieves enlightening education and improves enjoyment of the flight toy and satisfies the demands of the users.

A rotor of a motor includes a cylindrical portion, a first plate portion, a second plate portion, and a side hole. The cylindrical portion is arranged on a radially outer side with respect to the stator and extends in the axial direction. The first plate portion is arranged on a first axial side with respect to the stator, and expands radially inward from a first axial end of the cylindrical portion. The second plate portion is arranged on a second axial side with respect to the stator, and expands radially inward from a second axial end of the cylindrical portion. The side hole penetrates the cylindrical portion in a radial direction. The stator holder has a holder through-hole. The holder through-hole is arranged on the radially inner side with respect to the stator and penetrates the stator holder in the axial direction.

Concepts and technologies disclosed herein are directed to intelligent drone traffic management via a radio access network (“RAN”). As disclosed herein, a RAN node, such as an eNodeB, can receive, from a drone, a flight configuration. The flight configuration can include a drone ID and a drone route. The RAN node can determine whether capacity is available in an airspace associated with the RAN node. In response to determining that capacity is available in the airspace associated with the RAN node, the RAN node can add the drone ID to a queue of drones awaiting use of the airspace associated with the RAN node. When the drone ID is next in the queue of drones awaiting use of the airspace associated with the RAN node, the RAN node can instruct the drone to fly through at least a portion of the airspace in accordance with the drone route.

According to one embodiment, a movement instruction device and a method capable of avoiding a risk when a movable object moves are provided. The movement instruction device includes: a storage device that stores map information for determining a movement path of an indoor movable object to a destination; and a processor that sets a movement prohibition area of the movable object in the map information based on information on an obstacle obtained from outside, and reviews the movement path of the movable object based on a current position, the destination, and the set movement prohibition area of the movable object.

An aeronautical vehicle that rights itself from an inverted state to an upright state has a self-righting frame assembly has a protrusion extending upwardly from a central vertical axis. The protrusion provides an initial instability to begin a self-righting process when the aeronautical vehicle is inverted on a surface. A propulsion system, such as rotor driven by a motor can be mounted in a central void of the self-righting frame assembly and oriented to provide a lifting force. A power supply is mounted in the central void of the self-righting frame assembly and operationally connected to the at least one rotor for rotatably powering the rotor. An electronics assembly is also mounted in the central void of the self-righting frame for receiving remote control commands and is communicatively interconnected to the power supply for remotely controlling the aeronautical vehicle to take off, to fly, and to land on a surface.

A power conversion unit may include two or more power modules for providing high-voltage direct current power to electrical loads, such as one or more propulsion motors aboard an aerial vehicle. Each of the power modules may be controlled by hysteresis, and may include one or more pairs of transistors that are switched by a gate driver with respect to differences between a reference current and a sensed current passing through a boost inductor. The number, size and shape of the power modules may be selected to accommodate the electrical loads, and may be switched on or off, as necessary. The power conversion unit may feature at least one more power module than is required to meet all anticipated electrical loads, thereby ensuring that the power conversion unit may continue to provide power even in the event that one of the power modules experiences a fault of any kind.

An unmanned aerial vehicle according to the present invention includes: a main body; an arm that extends from the main body to support a rotor; a first electrical conductor which is supported by the arm and to which a voltage is applied; a second electrical conductor which is supported by the arm and spaced apart from the first electrical conductor and to which a voltage lower than the voltage applied to the first electrical conductor is applied; and a controller configured to control electrical supply to the first and second electrical conductors.

A supporting wing structure for an aircraft, in particular for a load-carrying and/or passenger-carrying aircraft, preferably an aircraft in the form of a vertical take-off and landing multicopter having a plurality of electrically driven rotors which are disposed in a distributed manner. The supporting wing structure has a plurality of struts. A first number of the struts are at least largely disposed in a first direction, while a second number of the struts are at least largely disposed in a second direction, the second direction being oriented orthogonal to the first direction. At least the struts of the second number have an aerodynamic profile in cross section, and/or in the struts are connected to one another at least in pairs between neighboring struts by a connecting structure, preferably from individual connecting segments, and the connecting structure or the connecting segments have an aerodynamic profiling. Furthermore an aircraft is provided equipped with such a supporting wing structure.

A fail safety apparatus of the air mobility is provided. Locations of propeller modules are adjusted by rotation parts and length adjustment units to evenly distribute thrust of the re-located propeller modules so that the attitude of the air mobility is stabilized. In particular, when one propeller module among a plurality of propeller modules fails, the attitude of the air mobility is normalized by adjusting a location of the failed propeller module and locations of remaining normal propeller modules so that flight safety of the air mobility is secured.