An unmanned aerial vehicle (UAV) that includes: a front chassis defining an intake port; a rear chassis defining an exhaust port and providing a heatsink for the UAV; and a blower that is located immediately rearward of the intake port so as to facilitate unobstructed airflow through the intake port and into the blower. The blower is configured to direct air through the UAV along an airflow path that extends from the intake port to the exhaust port to thereby cool the UAV.

An unmanned aerial vehicle (UAV) that includes: a front chassis defining an intake port; a rear chassis defining an exhaust port and providing a heatsink for the UAV; and a blower that is located immediately rearward of the intake port so as to facilitate unobstructed airflow through the intake port and into the blower. The blower is configured to direct air through the UAV along an airflow path that extends from the intake port to the exhaust port to thereby cool the UAV.

The battery thermal management system includes a battery pack, a circulation subsystem, and a heat exchanger. The system can optionally include a cooling system, a reservoir, a de-ionization filter, a battery charger, and a controller.

The battery thermal management system includes a battery pack, a circulation subsystem, and a heat exchanger. The system can optionally include a cooling system, a reservoir, a de-ionization filter, a battery charger, and a controller.

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.

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.

The present invention relates to an apparatus and method for capturing energy from an unmanned aircraft propeller system and utilizing the energy to charge a battery. The invention further provides for a belt drive system connected to one or more propellers of an unmanned aircraft system commonly referred to as a drone aircraft. The belt drive system may be linked to an alternator or dynamo such that a portion of the energy generated by the rotation force provided to the drive system of the propeller is captured by the alternator or dynamo. The present invention provides for a system where the rotational energy of the propellers is captured by an energy recovery system such as an alternator, dynamo or the like. The energy recovery system provides power to charge a battery which can be used to power the drive systems for the propellers, or other electronic systems.

The present invention relates to an apparatus and method for capturing energy from an unmanned aircraft propeller system and utilizing the energy to charge a battery. The invention further provides for a belt drive system connected to one or more propellers of an unmanned aircraft system commonly referred to as a drone aircraft. The belt drive system may be linked to an alternator or dynamo such that a portion of the energy generated by the rotation force provided to the drive system of the propeller is captured by the alternator or dynamo. The present invention provides for a system where the rotational energy of the propellers is captured by an energy recovery system such as an alternator, dynamo or the like. The energy recovery system provides power to charge a battery which can be used to power the drive systems for the propellers, or other electronic systems.