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.

A mobile object includes a battery, a coolant, and a discharger. The coolant in a solid state is disposed around the battery and is liquefied by heat transferred from the battery. The discharger discharges the coolant liquefied out of the mobile object.

A mobile object includes a battery, a coolant, and a discharger. The coolant in a solid state is disposed around the battery and is liquefied by heat transferred from the battery. The discharger discharges the coolant liquefied out of the mobile object.

An apparatus for cooling an electric propulsion engine for an object, including a stator having a stator housing and a rotor, which is supported in a rotationally movable manner on the stator housing and is connected to a propulsion means for generating a force acting on the object, by a first coolant and a second coolant. The propulsion means generates a flow of the first coolant by rotational motion. The first coolant flows around or through the electric propulsion engine with aid of a flow guide, wherein the second coolant circulates in a cooling channel and transfers uptaken heat to the first coolant. The second coolant is circulated in the cooling channel with aid of a pump driven by the propulsion engine.

A liquid-curtain type heat dissipation structure for LiDAR onboard unmanned aerial vehicle, belonging to the field of LiDARs. The structure is used to solve the problem that the existing device onboard UAV is difficult to meet heat dissipation requirements of LiDAR onboard UAV due to limited energy source during operation. The structure is provided on a LiDAR box body, a liquid storage tank is built into the top of a box lid to store cooling liquid. Meanwhile, the liquid storage tank is provided with a vent hole and a liquid outlet, and the vent hole is used to control flow velocity of the cooling liquid. During operation, the cooling liquid flows out from the liquid outlet, is guided to a heat dissipation panel through a liquid guide groove, and is attached to a surface of a heat dissipation panel.

A liquid-curtain type heat dissipation structure for LiDAR onboard unmanned aerial vehicle, belonging to the field of LiDARs. The structure is used to solve the problem that the existing device onboard UAV is difficult to meet heat dissipation requirements of LiDAR onboard UAV due to limited energy source during operation. The structure is provided on a LiDAR box body, a liquid storage tank is built into the top of a box lid to store cooling liquid. Meanwhile, the liquid storage tank is provided with a vent hole and a liquid outlet, and the vent hole is used to control flow velocity of the cooling liquid. During operation, the cooling liquid flows out from the liquid outlet, is guided to a heat dissipation panel through a liquid guide groove, and is attached to a surface of a heat dissipation panel.