Shanghai Autoflight Co., Ltd.

Haoxiang Electric Energy (kunshan) Co., Ltd.

Autoflight (kunshan) Co. Ltd.

Yuneec Technology Co., Limited

Other

Yuneec International (china) Co., Ltd

Yujet International Corporation Limited

Shandong Dingfeng Aviation Technology Co., Ltd.

Pinnacle Vista, LLC

Autoflightx International Limited

Shanghai Helang Electronics Co., Ltd.

Yu Tian

Wenyan Jiang

Yongqiang Cui

Drone aircraft

A quick-release wing structure includes a lock cylinder assembly and a lock head. The lock cylinder assembly is installed in the fuselage. The lock cylinder assembly includes a shell and a lock plate. An installation slot is opened inside the shell. The side wall of the installation slot is provided with a clamping hole connected with the installation slot. The lock plate is sliding and arranged in the installation slot. The lock head is installed in the wing. A locking slot is set on the periphery of the lock head. The lock head can pass through the clamping hole and drive the lock plate to move. When the locking slot is facing the lock plate, the lock head is clamped onto the locking slot and fixed. The UAV includes the quick-release wing structure described above.

Quick-release wing structure and an unmanned aerial vehicle using the same

A motor-driven power board having a PCB and a plurality of transistors uniformly arranged along the edge of the PCB and a plurality of capacitors uniformly arranged along the inner side of the transistor. There is a plurality of terminals uniformly arranged along the inner side of the transistor. The board further includes a positive pole of power bus, a negative pole of power bus and a signal wire which are all located in the middle of the PCB. The invention improves the heat dissipation and current-sharing capacity of the power board by uniformly setting the power components from the inside to the outside according to the heat value while at the same time reduces the heat value in the middle of the power board, so that the motor of the driver using the power board can be assembled near the middle of the power board.

Motor-driven power board and a motor driver using the same

An aircraft motor driver having a power board and a motor, wherein the power board includes a base plate and a power element, and the power element is located at the edge of the base plate. The motor is located near the middle of the power board and is electrically connected to the terminal block on the base plate, and the motor driver is provided with an airflow circulation channel for providing the airflow used for heat dissipation of the power element. The aircraft motor driver arranges the power element on the outer edge of the power board, so that the motor of the driver can be assembled near the middle of the power board, reducing the assembly difficulty and assembly volume of the driver, and, so that the power board can be cooled by air cooling mode of air convection.

Aircraft motor driver

An unmanned aerial vehicle having a fuselage, a water collection and emission equipment, wings, linear reinforcements, a landing gear and a vertical fin. The water collection and emission equipment has buoyancy units, a sealed cabin, a water pump and a water collection and emission pipe. The sealed cabin is detachably connected to the fuselage, and a compartment is arranged in the sealed cabin. The water pump is arranged in the compartment and the side wall of the sealed cabin has at least one concave part which is concave towards the direction of the inner cavity used for slowing down the swaying of water.

Unmanned aerial vehicle

Drone

A method to test an unmanned aerial vehicle (UAV) using a support component, a universal rotating component, a fixed component and a return component. The method further includes wherein the universal rotating component slides along the Z direction and is arranged on the support component, and one end of the universal rotating component can rotate in a universal way relative to the other end of the universal rotating component. The fixed component is connected to one end of the universal rotating component, and the fixed component is configured to fix the UAV. One end of the return component is connected to the support component, the other end is connected to the other end of the universal rotating component, and the return component is configured to drive the universal rotating component and the fixed component to reset.

Method of testing an unmanned aerial vehicle (UAV) using a test bench

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.

Vertical tail for a composite-wing UAV

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.

Data monitoring method and medium

A vertical takeoff and landing aerial vehicle and a cooling system for the aerial vehicle. The vertical takeoff and landing aerial vehicle comprises at least one air inlet provided on the top side of a linear support below a lift propeller, and at least one air outlet provided on the linear support. In the vertical takeoff and landing stage of the aerial vehicle provided by the disclosure, airflow generated by rotation of a lift propeller forms a rapid-flowing spatial flow field, which can achieve efficient heat dissipation of a motor and an electronic speed controller in an arm; and in the vertical takeoff and landing unmanned aerial vehicle provided by the utility, the takeoff weight of the unmanned aerial vehicle cannot be increased, power consumption of airborne equipment cannot be increased, and interior space of the arm cannot be occupied.

Growing community of inventors

Hong Kong, China

Yu Tian