Control assembly for aircraft propulsion systems

An aircraft propulsion system assembly comprising:

• a cockpit control system;
• an aircraft propulsion system including a propulsor, an engine, and an electrical assembly,
• the engine includes a rotational assembly configured for rotation about an engine rotational axis of the engine, and the rotational assembly is coupled to the propulsor, and
• the electrical assembly includes an electric motor, the electric motor includes a rotor, and the rotor is coupled to the propulsor;
• and
• a control assembly including a propulsion system sensor assembly, an electric motor sensor, a plurality of channel A control units, and at least one channel B control unit,
• the propulsion system sensor assembly includes a plurality of sensors configured to directly measure one or both of a propulsor rotation speed or a propulsor torque of the propulsor, and the propulsion system sensor assembly is connected in signal communication with the cockpit control system and the at least one channel B control unit;
• the electric motor sensor is configured to measure one or both of an electric motor rotation speed or an electric motor torque of the electric motor, and the electric motor sensor is connected in signal communication with the at least one channel B control unit;
• the plurality of channel A control units includes an engine control unit for the engine and an electric motor control unit for the electric motor, the engine control unit is configured to generate an output engine control signal for operation of the engine based on an input engine command signal from the cockpit control system, and the electric motor control unit is configured to generate an output electric motor control signal for operation of the electric motor based on an input electric motor command signal from the cockpit control system, and
• the at least one channel B control unit includes a processor connected in signal communication with non-transitory memory including instructions which, when executed by the processor, cause the processor to:
• identify an uncontrolled propulsor condition using one or both of the propulsor rotation speed or the propulsor torque;
• identify a source of the uncontrolled propulsor condition as one of the engine or the electric motor using one or both of the electric motor rotation speed or the electric motor torque;
• and
• control the source to shut down.

An aircraft propulsion system assembly comprising:

• a cockpit control system;
• an aircraft propulsion system including a propulsor, an engine, and an electrical assembly,
• the engine includes a rotational assembly configured for rotation about an engine rotational axis of the engine, and the rotational assembly is coupled to the propulsor, and
• the electrical assembly includes an electric motor, the electric motor includes a rotor, and the rotor is coupled to the propulsor;
• and
• a control assembly including a propulsion system sensor assembly, an electric motor sensor, a plurality of channel A control units, and at least one channel B control unit,
• the propulsion system sensor assembly includes a plurality of sensors configured to directly measure one or both of a propulsor rotation speed or a propulsor torque of the propulsor, and the propulsion system sensor assembly is connected in signal communication with the cockpit control system, the plurality of channel A control units, and the at least one channel B control unit;
• the electric motor sensor is configured to measure one or both of an electric motor rotation speed or an electric motor torque of the electric motor, and the electric motor sensor is connected in signal communication with the at least one channel B control unit;
• the plurality of channel A control units includes an engine control unit for the engine and an electric motor control unit for the electric motor, the engine control unit is configured to generate an output engine control signal for operation of the engine based on the one or both of the propulsor rotation speed and the propulsor torque, and the electric motor control unit is configured to generate an output electric motor control signal for operation of the electric motor based on one or both of the propulsor rotation speed and the propulsor torque, and
• the at least one channel B control unit includes a processor connected in signal communication with non-transitory memory including instructions which, when executed by the processor, cause the processor to:
• identify valid and invalid output control signals of the output engine motor control signal and the output electric motor control signal using the one or both of the propulsor rotation speed or the propulsor torque;
• identify an uncontrolled propulsor condition using one or both of the first propulsor rotation speed or the first propulsor torque;
• and
• identify a source of the uncontrolled propulsor condition as one of the engine or the electric motor using one or both of the electric motor rotation speed or the electric motor torque.