Propulsor reverse rotation protection for hybrid-electric aircraft propulsion systems

A propulsion system for an aircraft, the propulsion system comprising:

• a propulsor;
• an engine including a rotational assembly, the rotational assembly coupled with the propulsor;
• an electrical assembly including a battery, a motor control unit, an electric motor, and an electrical distribution system, the electrical distribution system configured to electrically interconnect the battery and the motor control unit, the electrical distribution system including a contactor electrically connected between the battery and the motor control unit, the contactor switchable between a closed state and an open state, the motor control unit electrically connected with the electric motor, the electric motor coupled with the propulsor;
• a controller connected in signal communication with the contactor, the controller including at least one control channel, the at least one control channel including a processing system including a processor connected in signal communication with a non-transitory memory including instructions which, when executed by the processor, cause the processor to:
• control the contactor in the closed state or the open state by generating and transmitting an open control signal or a close control signal to the contactor, respectively;
• and
• a reverse rotation protection circuit including a current sensor, the current sensor configured to measure an electrical current between the battery and the motor control unit, the reverse rotation protection circuit operable to identify a presence or an absence of a reverse current flow between the battery and the motor control unit using the measured electrical current and, in response to identifying the presence of the reverse current flow, generate and transmit a protection open control signal to the contactor to control the contactor to switch to the open state with the controller generating and transmitting either of the open control signal or the close control signal.

A propulsion system for an aircraft, the propulsion system comprising:

• a propulsor;
• an engine including a rotational assembly and a gear box, the rotational assembly including a bladed turbine rotor and a shaft connected to the bladed turbine rotor, the shaft coupled with the propulsor by the gear box;
• an electrical assembly including a battery, an electric motor, and an electrical distribution system, the electrical distribution system configured to electrically interconnect the battery and the electric motor, the electrical distribution system including a contactor electrically connected between the battery and the electric motor, the contactor switchable between a closed state and an open state, the electric motor including a rotor coupled with the propulsor by the gear box;
• and
• a reverse rotation protection circuit including a current sensor, the current sensor configured to measure an electrical current between the battery and a motor control unit, the reverse rotation protection circuit operable to identify a presence or an absence of a reverse current flow between the battery and the motor control unit using the measured electrical current and, in response to identifying the presence of the reverse current flow, generate and transmit a protection open control signal to the contactor to control the contactor to switch to the open state.