A method comprising: communicating signals and transmitting the signals. Communicating the signals from an operation system to a motor controller of an unmanned aerial vehicle (UAV). Transmitting the signals from the motor controller to motors of the UAV. Applying a smoothing filter to the signals transmitted from the motor controller to the motors of the UAV to generate filtered signals. Controlling the motors with the filtered signals so that the motors operate to control movement of the UAV.

A method comprising: communicating signals and transmitting the signals. Communicating the signals from an operation system to a motor controller of an unmanned aerial vehicle (UAV). Transmitting the signals from the motor controller to motors of the UAV. Applying a smoothing filter to the signals transmitted from the motor controller to the motors of the UAV to generate filtered signals. Controlling the motors with the filtered signals so that the motors operate to control movement of the UAV.

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.