Uncontrollable high thrust (UHT) protection for hybrid-electric aircraft propulsion systems

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

• a propulsor;
• an engine including an engine output shaft, a combustor, and a fuel system, the engine output shaft coupled with the propulsor, the fuel system connected in fluid communication with the combustor, the fuel system including a fuel control unit operable to control fuel flow from the fuel system to the combustor;
• an electrical assembly including an electric motor and a motor control unit, the electric motor coupled with the propulsor, the motor control unit electrically connected with the electric motor;
• an engine controller including a first controller channel, the first controller channel including a first processing system, the first processing system including a processor connected in signal communication with a non-transitory memory storing instructions which, when executed by the processor, cause the processor to:
• generate a first control signal output for the fuel control unit to direct fuel to the combustor, and
• generate a second control signal output for the motor control unit to direct electrical power to the electric motor;
• a sensor assembly including at least one propulsor sensor;
• and
• an uncontrollable high thrust (UHT) protection assembly including a first protection circuit of the first controller channel, the first protection circuit connected in signal communication with the at least one propulsor sensor, the first protection circuit operable to identify a presence or an absence of a UHT condition of the propulsor in response to one or both of a propulsor rotation speed or a propulsor torque from the at least one propulsor sensor and, in response to identifying the presence of the UHT condition, generate a shutdown signal for the fuel control unit and the motor control unit overriding the first control signal output and the second control signal output, the presence of the UHT condition identified by the first protection circuit where the one or both of the propulsor rotation speed or the propulsor torque is greater than a respective UHT threshold value.

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

• a propulsor;
• a gear box coupled with the propulsor;
• an engine including an engine output shaft, a combustor, and a fuel system, the engine output shaft coupled with the propulsor by the gear box, the fuel system connected in fluid communication with the combustor, the fuel system including a fuel control unit operable to control fuel flow from the fuel system to the combustor;
• an electrical assembly including an electric motor and a motor control unit, the electric motor coupled with the propulsor by the gear box, the motor control unit electrically connected with the electric motor;
• an engine controller including a first controller channel, the first controller channel includes a first processing system, the first processing system operable to control the fuel control unit to direct fuel to the combustor and to control the motor control unit to direct electrical power to the electric motor;
• a sensor assembly including at least one propulsor sensor disposed at the propulsor;
• and
• an uncontrollable high thrust (UHT) protection assembly including a first protection circuit of the first controller channel, the first protection circuit connected in signal communication with the at least one propulsor sensor, the first protection circuit operable to identify a presence or an absence of a UHT condition of the propulsor in response to one or both of a propulsor rotation speed or a propulsor torque from the at least one propulsor sensor and, in response to identifying the presence of the UHT condition, generate a shutdown signal for the fuel control unit and the motor control unit.