Abstract: A vertical tail of a composite-wing unmanned aerial vehicle (UAV) having a body, a rudder face section, a rotor section, shock absorbing component and a quick installation assembly of circuit. The body includes a tail body frame and a shell. The rudder face section has a rudder machine and a rudder surface. The rudder surface is connected to one end of the tail for steering the directional deflection of the UAV. The shock absorbing component is connected to the lower end plate and the shock absorbing component absorbs the shock to the body. The quick installation assembly of circuit includes a plug, a positioning sleeve and a bias piece, the positioning sleeve is located on the outer circumference of the plug and slidingly connected to the plug, the bias piece is set between the plug and the positioning sleeve, the bias piece can absorb the impact on the plug.

Abstract: A data monitoring method and a data monitoring medium. The method has: acquiring current vibration data of a target flight device in real time; Determining an anomaly protection strategy of the target flight device based on the current vibration data; The target flight equipment is controlled to execute corresponding operations according to an abnormality protection strategy. Embodiments of the invention, by acquiring the current vibration data of the target flight equipment in real time, determining an anomaly protection strategy of the target flight device based on the current vibration data.

Abstract: An aircraft and its connector where the connector has a first pluggable unit and a second pluggable unit, the end of the first pluggable unit is provided with several terminal pins, the end of the second pluggable unit is provided with several terminal sockets, and the terminal pin and the terminal socket can be operatively connected in a corresponding manner. The end of the first pluggable unit and the end of the second pluggable unit are also provided with an error-proof protrusion part and an error-proof concave part respectively. The error-proof protrusion part and the error-proof concave part are operatively connected in a corresponding manner.

Abstract: A plug-in assembly structure for a UAV includes a first component (1), a second component (2) and a limit assembly (3). The first component (1) includes a first plug (11) and a positioning sleeve (12), and the positioning sleeve (12) is provided with a first through hole (121). The second component (2) includes a second plug (21), the radial direction of the second plug (21) is provided with a limit hole (2111), the second plug (21) can be electrically connected to the first plug (11), and the limit hole (2111) is facing the first through hole (121). The limit assembly (3) is installed in the limit hole (2111). The limit assembly (3) includes a first elastic element (31) and a limit element (32).

Abstract: A transport vehicle and an unmanned aerial vehicle (UAV) having a head (1), a control assembly arranged in the head (1) used for controlling the movement state of the transport vehicle. The carrying plate (2) is connected to the head (1) to form an open carriage space so as to accommodate container (3). The container (3) is provided on the carrying plate (2) and at least comprises a base plate (31) and an opening (32). The base plate (31) is provided with an overturning assembly (4), the overturning assembly (4) is rotatably connected to the base plate (31) and is used for driving the piece to be transported to rotate from a first predetermined position around the side direction of the base plate (31) until the piece to be transported is arranged at a second predetermined position through the opening (32).

Abstract: A combined vertical takeoff and landing UAV having a large vertical takeoff and landing UAV, a connecting device, and a small vertical takeoff and landing UAV. The connecting device having a clamping component and an adsorption component. The clamping component includes a clamping part, and a clamping groove is arranged on the clamping part. The clamping component having a snap-fitting part, and a snap-fitting groove is arranged on the snap-fitting part. The clamping groove and the snap-fitting groove are correspondingly set. A first holding space is arranged on the clamping part, and a second holding space is arranged on the snap-fitting part. The adsorption component comprises a first magnetic element located in the first holding space, and the adsorption component also comprises a second magnetic element, which is located in the second holding space.

Abstract: An aircraft transport trailer having a frame, a wheel assembly, a lower bracket, and an upper bracket. The wheel assembly is rotationally installed on the frame to support and move the frame. The lower bracket is fixedly installed on the frame, and the top of the lower bracket is provided with a body slot. The preset first surface of the inner wall of the body slot is fitted with the part of the lower surface of the body, the aircraft body can be partially seated in the aircraft body slot under the action of gravity.

Abstract: A UAV body and a delivery structure, wherein the delivery structure has a mounting piece, a reset assembly and a limiting piece. The reset piece deforms when the piece to be transported is lifted, which resets to drive the piece to leave the mounting groove when the piece to be transported touches the ground. The first end of the limiting piece is connected to the reset piece, and when the piece to be transported is not lifted, the second end of the limiting piece can be connected to the mounting piece by magnet to seal the opening of the mounting groove. The reset piece drives the limiting piece to move so as to separate the second end from the mounting piece when the piece to be transported is lifted.