A system and method for a mobile hybrid transmitter/receiver (TX/RX) node for wireless resonant power delivery is disclosed. A hybrid TX/RX can be configured to travel to remote, wirelessly-powerable receivers and deliver power to them wirelessly. A hybrid TX/RX device can include a transmitter component (TX), a receiver (RX) component, and a power store for storing power for supply to remote receivers. The TX/RX device can be configured in an autonomous unmanned vehicle operational to travel between a fixed source transmitter devices and one or more specified locations that may be host to one or more remote receivers. In the location of the one or more remote receivers, the TX component may function to wirelessly transfer power from the power store to the one or more remote receivers. In the location of the fixed source transmitter device, RX component can be configured to receive power via wireless power transfer, and to use the received power to at least partially replenish the power store.

An unmanned aerial vehicle may include a flight control circuit configured to control flight of the unmanned aerial vehicle and to provide a flight path based at least on an actual position of the unmanned aerial vehicle and a desired target position for the unmanned aerial vehicle; and at least one sensor configured to monitor an environment of the unmanned aerial vehicle and to detect one or more obstacles in the environment; wherein the flight control circuit is further configured to determine a local flight path to avoid a collision with one or more detected obstacles, and to superimpose the flight path with the local flight path, thereby generating a flight path to the desired target position avoiding a collision with the one or more detected obstacles.

According to one embodiment, a flying body includes a radar, a supporter, a plurality of rotors supported by the supporter, and a controller. The rotors include a first rotor. The radar is configured to perform a detection operation and a non-detection operation. The controller is configured to perform a first control operation in a first transition from the non-detection operation to the detection operation. The controller is configured to perform a first change in the first control operation to change a rotational speed of the first rotor from a rotational speed of the first rotor in the non-detection operation. The detection operation is performed after the first control operation.

According to one embodiment, a flying body includes a radar, a supporter, a plurality of rotors supported by the supporter, and a controller. The rotors include a first rotor. The radar is configured to perform a detection operation and a non-detection operation. The controller is configured to perform a first control operation in a first transition from the non-detection operation to the detection operation. The controller is configured to perform a first change in the first control operation to change a rotational speed of the first rotor from a rotational speed of the first rotor in the non-detection operation. The detection operation is performed after the first control operation.

An underwater and aerial vehicle includes a fixing frame, a core navigation system and an energy supply system. The fixing frame has a circular ring configuration in a middle part thereof, and the waterproof sealing cabin is fixed in the circular ring configuration, and multiple cantilever arms extend around the circular ring configuration. An underwater navigation control module and a relay are provided on an auxiliary fixing platform. A second brushless motor is provided on each of the cantilever arms. Each second brushless motor is provided with a marine propeller. A flight control module, a remote control receiver and a power management module are provided on a fixing platform. A first brushless motor is provided on each of the cantilever arms. Each first brushless motor is provided with a rotor via a coupling. The energy supply system is arranged in a lower part of the waterproof sealing cabin.

The present invention discloses an unmanned aerial vehicle, including: a fuselage; a battery accommodation cavity, disposed on the fuselage; a battery pack, including at least two battery blocks and mounted inside the battery accommodation cavity; a battery circuit board, electrically connected to the battery blocks in the battery pack; and a functional module, electrically connected to the battery circuit board, the battery blocks in the battery pack supplying power to the functional module via the battery circuit board at the same time. By using the solution of the present invention, endurance of the unmanned aerial vehicle is increased.

The drone comprises M antennas, with in particular two offset antennas located symmetrically at the ends of two arms for the connection to the propulsion units (24), and a ventral antenna under the drone body. The radio transmission is operated simultaneously on N similar RF channels, with 2N<M. An antenna switching circuit couples selectively each of the N RF channels to N antennas out of the M antennas according to a plurality of different coupling schemes, dynamically through a piloting logic selecting one of the coupling schemes. The selection is operated as a function of a signal delivered by the drone-borne microprocessor, as a function of the flight and signal transmission conditions, determined at a given instant.

The present disclosure is directed to unmanned aerial vehicle (UAV) comprising a convertible body operably coupled to at least one sensor, and further configured to rotate at least about a longitudinal axis, thereby providing a full field of regard for the at least one sensor, and a plurality of arms extending laterally from the convertible body, each arm of the plurality of arms having a rotor assembly coupled thereto.

An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.

An unmanned aerial vehicle (UAV) includes a fuselage, a pair of wings attached to the fuselage, and a propulsion system mounted to the wings to provide propulsion to the UAV. The fuselage has an outer fuselage shell that is a first mechanical support structure for an airframe of the UAV. The pair of wings is attached to the fuselage and shaped to provide aerodynamic lift. The wings have outer wing shells that are second mechanical support structures for the airframe. The outer fuselage shell or the outer wing shells comprise one or more formed-metal sheets.