An unmanned air vehicle is provided. The unmanned air vehicle includes one or more generators, each of which generates a force that drives the unmanned air vehicle to fly and also generates an airflow. Each of one or more first microphones is located in an external region that is not included in any of one or more first airflow regions. Each of the one or more first airflow regions corresponds to the airflow generated by one of the one or more generators. Each of one or more second microphones is located in the external region between at least one of the one or more generators and the one or more first microphones. A processor performs processing on one or more first signals output from the one or more first microphones and one or more second signals output from the one or more second microphones.

A system includes an aerial drone with a queen component disposed thereon and an underwater robot with a worker component disposed thereon. The queen component is in electrical communication with the aerial drone and the worker component is in electrical communication with the underwater robot. The queen component is configured to steer a laser beam to locate and track the worker component and to sense light from the laser beam reflected by the worker component. A method includes deploying an aerial drone with a queen component disposed thereon in a first medium and determining a location of a robot in a second medium with a worker component disposed thereon using the aerial drone. The second medium is different from the first medium.

A system includes an aerial drone with a queen component disposed thereon and an underwater robot with a worker component disposed thereon. The queen component is in electrical communication with the aerial drone and the worker component is in electrical communication with the underwater robot. The queen component is configured to steer a laser beam to locate and track the worker component and to sense light from the laser beam reflected by the worker component. A method includes deploying an aerial drone with a queen component disposed thereon in a first medium and determining a location of a robot in a second medium with a worker component disposed thereon using the aerial drone. The second medium is different from the first medium.

The present disclosure provides a frame assembly for an unmanned aerial vehicle. The frame assembly comprises a housing having an electric chamber and a circuit board assembly disposed in the electric chamber and including a first circuit board and a second circuit board. The electric chamber has an upper opening and a lower opening; and the first circuit board is installed in the electric chamber via the upper opening, and the second circuit board is installed in the electric chamber via the lower opening and spaced apart from the first circuit board.

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.

A battery assembly includes a battery body, a housing, a switch assembly, an output terminal, and a snap clip assembly. The housing includes an accommodation chamber. The battery body is mounted in the accommodation chamber. The switch assembly is fixed at the housing and configured to generate an in-position signal. The output terminal is arranged at the housing and configured to output power of the battery body and the in-position signal. The snap clip assembly is arranged at the housing and configured to cause the switch assembly to be in a first status when no external force is applied to the snap clip assembly, the in-position signal being at a first level in the first status, and when an external force is applied to the snap clip assembly, cause the switch assembly to be in a second status, the in-position signal being at a second level in the second status.

A linear thruster aircraft includes: an airframe, including an elongated mounting nacelle and a main body; an aircraft control unit with a processor, a non-transitory memory, and an input/output component; and at least one linear thruster arrangement with at least four thrusters mounted along at least one elongated axis of the elongated mounting nacelle, such that the thrusters are configured to provide lift, pitch, roll, and yaw movement. Optionally, the linear thruster arrangement can include alternating lateral and vertical offsets of the thrusters from the elongated axis, and pairs of thrusters can be vertically overlapping.

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 technology described herein relates to autonomous aerial vehicle technology and, more specifically, to autonomous unmanned aerial vehicle with folding collapsible arms. In some embodiments, a UAV including a central body, a plurality of rotor arms, and a plurality of hinge mechanisms is disclosed. The plurality of rotor arms each include a rotor unit at a distal end of the rotor arm. The rotor units are configured to provide propulsion for the UAV. The plurality of hinge mechanisms mechanically attach (or couple) proximal ends of the plurality of rotor arms to the central body. Each hinge mechanism is configured to rotate a respective rotor arm of the plurality of rotor arms about an axis of rotation that is at an oblique angle relative to a vertical median plane of the central body to transition between an extended state and a folded state.

The technology described herein relates to autonomous aerial vehicle technology and, more specifically, to image stabilization systems for autonomous aerial vehicles. In some embodiments, a UAV including a central body, an image capture assembly that couples the image capture assembly to the central body. The image stabilization assembly is configured to provide structural protection and support around the image capture assembly while passively isolating the image capture assembly from vibrations and other motion of the central body while the UAV is in flight.