A UAV heatsink assembly including two heat pipes, a first and second heat pipes including transfer and end portions, the end portions thermally connected to first and second metallic heat transfer elements, and a third metallic heat transfer element thermally connected to opposite ends of the heat pipes. A CPU thermally connected to the third metallic heat transfer element with first and second electrically insulating thermoplastic elements into which the respective first and second metallic components fit where the first and second electrically insulating thermoplastic elements are not between an outside ambient environment and the first and second metallic components. The heat pipes each include a wick structure and an embedded liquid providing thermal transport therein while at least some of the embedded liquids are above a threshold temperature between ?40? C. and 70? C. such that the UAV is at least operable above ?40? C. degrees and below 70? C.

A UAV heatsink assembly including two heat pipes, a first and second heat pipes including transfer and end portions, the end portions thermally connected to first and second metallic heat transfer elements, and a third metallic heat transfer element thermally connected to opposite ends of the heat pipes. A CPU thermally connected to the third metallic heat transfer element with first and second electrically insulating thermoplastic elements into which the respective first and second metallic components fit where the first and second electrically insulating thermoplastic elements are not between an outside ambient environment and the first and second metallic components. The heat pipes each include a wick structure and an embedded liquid providing thermal transport therein while at least some of the embedded liquids are above a threshold temperature between ?40? C. and 70? C. such that the UAV is at least operable above ?40? C. degrees and below 70? C.

The disclosure relates to a propeller drive that is, in particular, an aircraft drive and includes a propeller machine and an electric drive connected without a converter to the propeller machine. The aircraft includes such a propeller drive.

Provided are a stator, and a propeller driving device and an aircraft using the stator. The propeller driving device includes: a radial gap type BLDC motor with an inner rotor-outer stator structure where a rotor is placed in a circumferential shape with an air gap inside a stator; and a propeller installation bracket for mounting a propeller to a rotary shaft of the motor, wherein the stator includes: a stator core including an annular back yoke having a predetermined width to form a magnetic circuit and teeth extending from the back yoke in a central direction; an insulator formed to surround an outer circumferential surface on which a coil is wound in each tooth; and a stator coil wound around an outer circumferential surface of the insulator in each tooth. The insulator is formed of an insulating heat dissipation composite material having both heat dissipation performance and insulation performance.

A gimbal includes a base and a first support rotatably provided on the base; the first support is in an L-shape and includes a first arm and a second arm constructing the L shape, the first arm is rotatably connecting with the base; and the second arm includes a first electric motor fixing structure. An unmanned aerial vehicle including the gimbal is also provided.

A cooling system includes a rotor (VTOL rotor, cruise rotor) for generating at least one of lift or thrust of an aircraft, a component group formed of a plurality of electrical components for rotating the rotor, and a cooling circuit for cooling the component group, wherein a plurality of the component groups corresponding to a plurality of the rotors are provided, and the plurality of component groups are cooled by the same cooling circuit.

A cooling system includes a rotor (VTOL rotor, cruise rotor) for generating at least one of lift or thrust of an aircraft, a component group formed of a plurality of electrical components for rotating the rotor, and a cooling circuit for cooling the component group, wherein a plurality of the component groups corresponding to a plurality of the rotors are provided, and the plurality of component groups are cooled by the same cooling circuit.

A flying apparatus includes a main body assembly, an arm extending from the main body assembly, a rotor attached to the arm, a driver to drive the rotor, and a cooling system to water-cool the driver. The cooling system includes a cooler to cool a coolant supplied to the driver, and a pump to cause the coolant to circulate between the cooler and the driver. The pump is located below the main body assembly.

A flying apparatus includes a main body assembly, an arm extending from the main body assembly, a rotor attached to the arm, a driver to drive the rotor, and a cooling system to water-cool the driver. The cooling system includes a cooler to cool a coolant supplied to the driver, and a pump to cause the coolant to circulate between the cooler and the driver. The pump is located below the main body assembly.

The present disclosure is directed to systems and methods for cooling an electric aircraft. The system comprises an electronic device, a casing, at least one fin, and at least one PHP. The electronic device can generate heat. The electronic device can be housed within the casing. The fin can be attached to the outer wall of the casing. The PHP can be embedded within the fin, such that an evaporator section of the PHP is closest to the heat source and the condenser section of the PHP is furthest from the heat source. The PHP can also be placed within the casing. In some embodiments, the casing can have a plurality of slots. The fin can be shaped such that a single fin may slide into a pair of slots and come to rest adjacent to the casing, wherein a PHP can be embedded within the fin.