A battery-powered aerial vehicle has a central controller, one or more propelling modules, and one or more battery assemblies for powering at least the one or more propelling modules. The battery assemblies are at a distance away from the central controller for reducing electromagnetic interference to the central controller. In some embodiments, the aerial vehicle is a fixed-wing unmanned aerial vehicle (UAV) having a central controller, a plurality of rotor units, and one or more battery assemblies. The central controller is in a center unit and the propelling modules are in respective rotor units. Each battery assembly is in a rotor unit in proximity with the propelling module thereof. In some embodiments, the central controller also has a battery-power balancing circuit for balancing the power consumption rates of the one or more battery assemblies.

A highly safe drone is provided. A remote controller and a drone are connected to each other through a network and cooperate to operate. The drone includes a flight control unit, a flight start command reception unit receiving a flight start command from a user, a drone determination unit determining a configuration of the drone itself, an external environment determination unit determining an external environment of the drone. The drone system has a plurality of states including a takeoff diagnosis state and satisfies a condition transitioning to another state. The takeoff diagnosis state includes a drone determination state where the drone determination unit determines the configuration of the drone itself and an external environment determination state where the external environment determination unit determines the external environment. The drone system makes the drone to takeoff after transitioning to the takeoff diagnosis state upon receiving the flight start command.

A dual-rotor wing motor includes a sleeve separating an inner shaft from an outer shaft. An external bearing is independently coupled to a shaft cover while an internal bearing is independently coupled to the inner shaft, and thus the external bearing and the internal bearing independently bear a friction force due to the rotation of the respective single shaft, the heat generated by the friction force can be reduced and the lubricant cannot be easily evaporated. Accordingly, the service life of the dual-rotor wing motor of the present invention can be prolonged.

A collapsible flying device is provided having a housing including first and second housing sections forming an enclosure, and a motorized assembly that includes a drive motor and a drive shaft driven by the drive motor. The drive shaft matingly receives the first housing section and is coupled to the second housing section, wherein operation of the drive motor drives the drive shaft to move the first housing section from a closed position adjacent the second housing section to an open position spaced from the second housing section. A rotor hub is rotatingly driven by the drive motor. At least two rotor blades are coupled thereto and positioned within the enclosure in a collapsed position when the first housing section is in the closed position, and extend beyond the enclosure in an expanded position when the first housing section is in the open position.

A tethered aerial vehicle, connected to an anchorage system in the ground level through a cord, comprising a pair of fixed wings; and a drive assembly. The drive assembly comprises actuators configured to tilt the propeller's axle. The fixed wings define a center hole located close to a gravitational center of the aerial vehicle. Within the edges of the center hole located close to the gravitational center of the aerial vehicle is a gimbal anchored to the fixed wings structure. The drive assembly is located within the edges of the center hole and attached to the gimbal in a manner that the gimbal interfaces the connection between the fixed wings and the drive assembly. The drive assembly consists of coaxial propellers mounted on the same axle driven by a counterrotating motor. The coaxial propellers are configured to rotate in opposite directions with respect to each other.

A passenger transport system has a pod adapted to carry passengers or articles and a first attachment interface, a plurality of transport vehicles, each adapted to couple to the passenger pod, a first entry station adapted to load a passenger or articles into the pod, a plurality of exchange points, and a final destination station adapted to unload the passenger or articles from the pod carried by the transport vehicle. The pod with a passenger or articles is loaded at the first entry station travels on transport vehicles between individual ones of the exchange stations, until arriving at the final destination station where the passenger or the articles are unloaded, the passenger or articles remaining in the pod through all exchanges between transport vehicles.

The present disclosure provides a multi-rotor Aerial Vehicle comprising at least five arms. Pairs of coaxial contra rotating rotors/propellers are configured on each arm defining a polygon. In the event of failure of any one of the rotors/propellers, a control system incorporating an autopilot, shuts off corresponding contra rotating rotor/propeller of the pair to maintain yaw stability thereby rendering the corresponding arm non-functional; and adjusts throttles of the coaxial contra rotating rotors/propellers of remaining functional arms to maintain tilt and lift stability of the Aerial Vehicle.

A foldable wing system for an unmanned aerial system having a fuselage includes a left wing frame having an inboard gear rotatably coupled to the fuselage, a right wing frame having an inboard gear rotatably coupled to the fuselage and a wing actuator coupled to a linkage point on at least one of the wing frames. The wing frames are movable between a plurality of positions including a deployed position and a stowed position. The inboard gear of the left wing frame is engaged with the inboard gear of the right wing frame such that the wing frames move symmetrically between the plurality of positions in response to movement of the linkage point by the wing actuator.

An unmanned aerial vehicle includes a fuselage body and a lift mechanism. The lift mechanism includes a rotor blade assembly and a rotary driving member and defines an axis of rotation. The lift being mechanism is coupled to the fuselage body. The rotary driving member is configured to controllably rotate the rotor blade assembly about the axis of rotation. The rotor blade assembly includes at least one rotor blade. The at least one rotor blade including a vortex generator defined along an upper surface of the rotor blade.

An unmanned aerial signal relay includes an unmanned aerial vehicle, including a communication relay unit and at least one antenna, communicatively connected to the communication relay unit; a tether comprising at least two wires and at least one fiber optic cable, the wires and cable communicatively connected to the unmanned aerial vehicle; and a surface support system comprising a spool physically connected to the tether and a ground-based receiver communicatively connected to the at least one fiber optic cable, wherein the unmanned aerial vehicle is powered by electrical energy provided by the at least two wires, and wherein the communication relay unit is configured to relay signals received from the at least one antenna via the fiber optic cable to the ground-based receiver. Various systems and methods related to an unmanned aerial signal relay are also described.