Systems and methods for controlling an electrical distribution system for a hybrid-electric aircraft propulsion system

Abstract

A propulsion system for an aircraft includes a propulsor, an engine, and an electrical distribution system. The engine includes a first rotor and a first shaft. The first shaft is connected to the first rotor. The electrical distribution system includes a low-voltage bus, a high-voltage bus, a low-voltage generator, a DC:DC converter, and an electric motor. The low-voltage generator is coupled to the first shaft and electrically connected to the low-voltage bus. The low-voltage generator is configured to generate low-voltage electrical power and supply the low-voltage electrical power to the low-voltage bus. The DC:DC converter is electrically connected to the low-voltage bus and the high-voltage bus. The DC:DC converter is configured to convert the low-voltage electrical power to high-voltage electrical power and supply the high-voltage electrical power to the high-voltage bus. The electric motor is electrically connected to the high-voltage bus. The electric motor is configured to drive rotation of the propulsor.