A deployable clasping system is configured to be deployed from a component and securely clasp and release an object. The deployable clasping system includes a cable that is deployable from the transit vehicle. A clasp assembly is coupled to the cable. The clasp assembly is configured to securely clasp the object. A propulsion sub-system is coupled to one or both of the cable and the clasp assembly. The propulsion sub-system is configured to maneuver the clasp assembly to the object.

A method for processing image information in an image to determine a movement for a movable object. The method includes detecting whether the image includes a water surface or a sky based on the image information in the image, And, in response to detecting that the image includes the water surface or the sky, determining a technique from a plurality of techniques for calculating a depth map, generating the depth map using the technique, and determining a movement parameter for the movable object using the depth map.

An inertia measure unit (IMU) includes a main circuit board, and first and second weight blocks. A first surface of the first weight block contacts the main circuit board. The first weight block includes a recess formed on a second surface thereof opposite to the first surface, and an opening formed on a side surface thereof. The second weight block is coupled to the first weight block on the second surface to cover the recess. The first and second weight blocks jointly form an inner chamber in communication with the opening. The IMU further includes a circuit board disposed in the inner chamber, and a signal line coupled to an edge of the circuit board and extending out of the opening. The signal line bends over an outer surface of the first weight block or the second weight block to connect to the main circuit board.

A load control method and device based on a UAV, and a UVA. The UVA includes: a UVA body, a propeller arm with a first end connected to the UVA body, a propeller blade connected to a second end of the propeller arm and a processor installed in the UVA body; a length of the propeller arm and a size of the propeller blade are adjustable. The control method includes: determining load gravity of the UVA based on a carrying object of the UVA; determining a target lift of the UVA based on the load gravity; determining a target size of the propeller blade and a target length of the propeller arm based on the target lift; and adjusting the propeller arm to the target length and the propeller blade to the target size, so that the UVA controls the propeller blade to rotate to carry the carrying object.

A power driver of an unmanned aerial vehicle is disclosed and includes a main body, a fluid actuation system and a controller, wherein the fluid actuation system includes a driving zone, a converging chamber, a plurality of valves and a fluid discharging zone. The driving zone includes a plurality of flow guiding units which arranged in series, parallel or series-parallel, each of the flow guiding unit generates an inside pressure gradient after being actuated, so as to inhale fluid and diverge fluid by guiding channels, and flow into the convergence chamber for storage, wherein the amount of the fluid transported is controlled by the plurality of valves disposed in the connection channels through the controller, and fluid is finally converged to the fluid discharging zone for discharging the specific transportation amount of fluid.

An unmanned aerial vehicle (UAV) includes a central body and a plurality of arms extending from the central body. Each of the plurality of arms supports one or more propulsion units. At least one arm of the plurality of arms is configured to transform between (1) a flight configuration that provides lift while the UAV is in flight and (2) a landing configuration in which the at least one arm is configured to function as a landing support that bears weight of the UAV while the UAV is not in flight. The at least one arm is configured to transform between the flight configuration and the landing configuration in response to operation of the one or more propulsion units supported by the at least one arm.

An inertia measurement unit including a housing assembly, a weight block assembly, a circuit board, and a signal line. The housing assembly includes a cavity and a first opening in communication with the cavity. The weight block assembly is arranged in the cavity of the housing assembly. The weight block assembly includes an inner chamber and a second opening in communication with the inner chamber. The circuit board is arranged in the inner chamber of the weight block assembly. The signal line is coupled to a first edge of the circuit board and extends out of the weight block assembly through the second opening and out of the housing assembly through the first opening. At least one of the first opening or the second opening is located proximal to a second edge of the circuit board that is different from the first edge of the circuit board.

A method executable by a first device for instructing a second device to adjust attitude includes determining a first directional vector of the second device relative to the first device. The method also includes transmitting an attitude adjustment instruction to the second device. The attitude adjustment instruction includes directional data indicating the first directional vector or directional data derived based on the first directional vector. The attitude adjustment instruction is configured to instruct the second device to adjust the attitude based on the directional data indicating the first directional vector or the directional data derived based on the first directional vector.

Aerial vehicles are provided with one or more transformable arms (110, 310, 410, 510, 910). The one or more transformable arms (110, 310, 410, 510, 910) may support one or more propulsion units, and transform between a flight configuration where the propulsion units of the arms effect flight of the aerial vehicle, and a landing configuration, wherein the transformable arms (110, 310, 410, 510, 910) are used as a landing support that bears weight of the aerial vehicle when the aerial vehicle is not in flight. Using the transformable arms (110, 310, 410, 510, 910) as legs when the UAV is in a landed state permits the UAV to reduce weight and reduce obstruction to a payload carried by the UAV when the UA is in flight.

A method includes receiving, by a first receiver communicatively coupled with a first remote control device, a first control signal from the first remote control device. The method also includes receiving, by a second receiver communicatively coupled with a second remote control device, a second control signal from the second remote control device. The method further includes selecting one of the first control signal of the first remote control device and the second control signal of the second remote control device for controlling a movable object.