A propulsion system for an aircraft includes an air intake, an engine assembly, a turbocompressor, an electrical assembly, and at least one propulsor. The engine assembly includes an engine. The engine includes an air inlet, an exhaust outlet, and an engine output shaft. The turbocompressor assembly includes a turbocompressor. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The shaft interconnects the bladed turbine rotor and the bladed compressor rotor. The turbine includes a turbine inlet and a turbine outlet. The turbine inlet is connected in fluid communication with the exhaust outlet. The compressor includes a compressor inlet and a compressor outlet. The compressor inlet is connected in fluid communication with the air intake. The rotational assembly is mechanically independent of the engine output shaft.

A propulsion system for an aircraft includes an air intake, an engine assembly, a turbocompressor, an electrical assembly, and at least one propulsor. The engine assembly includes an engine. The engine includes an air inlet, an exhaust outlet, and an engine output shaft. The turbocompressor assembly includes a turbocompressor. The turbocompressor includes a turbine and a compressor. The turbine and the compressor form a rotational assembly. The rotational assembly includes a shaft, a bladed turbine rotor of the turbine, and a bladed compressor rotor of the compressor. The shaft interconnects the bladed turbine rotor and the bladed compressor rotor. The turbine includes a turbine inlet and a turbine outlet. The turbine inlet is connected in fluid communication with the exhaust outlet. The compressor includes a compressor inlet and a compressor outlet. The compressor inlet is connected in fluid communication with the air intake. The rotational assembly is mechanically independent of the engine output shaft.

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.

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.

An unmanned aerial vehicle includes a body, a first wing, a second wing, a first rotor assembly, a third rotor assembly, and a fourth rotor assembly. The body has a first accommodating cavity and a second accommodating cavity. The first wing and the second wing are disposed on two sides of the body. The first rotor assembly is mounted to the first wing, and the second rotor assembly is mounted to the second wing. The third rotor assembly includes a third motor and a third propeller connected to the third motor. The third motor is mounted in the first accommodating cavity and partially exposed to the body. The fourth rotor assembly includes a fourth motor and a fourth propeller connected to the fourth motor. The fourth motor is mounted in the second accommodating cavity and partially exposed to the body.

An unmanned aerial vehicle includes a body, a first wing, a second wing, a first rotor assembly, a third rotor assembly, and a fourth rotor assembly. The body has a first accommodating cavity and a second accommodating cavity. The first wing and the second wing are disposed on two sides of the body. The first rotor assembly is mounted to the first wing, and the second rotor assembly is mounted to the second wing. The third rotor assembly includes a third motor and a third propeller connected to the third motor. The third motor is mounted in the first accommodating cavity and partially exposed to the body. The fourth rotor assembly includes a fourth motor and a fourth propeller connected to the fourth motor. The fourth motor is mounted in the second accommodating cavity and partially exposed to the body.

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.

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.