Systems and methods for controlling an electric motor of an aircraft propulsion system
A propulsion system for an aircraft includes a propulsor, an engine, an electrical assembly, and a control unit. The engine includes a rotational assembly. The rotational assembly is coupled to the propulsor. The electrical assembly includes an electric motor, an electrical distribution system, and an electrical current sensor. The electric motor is coupled to the propulsor. The electric motor is electrically connected to the electrical distribution system. The electrical current sensor is configured to measure an electrical current supplied to the electric motor by the electrical distribution system. The control unit is configured to identify a power lever angle of a power throttle for the propulsion system is greater than or less than a power threshold, identify the electrical current is greater than or less than an electrical current threshold in response to identifying the power lever angle is less than the power threshold, and disable the electric motor in response to identifying the electrical current is greater than the electrical current threshold.
1 . A propulsion system for an aircraft, the propulsion system comprising:
a propulsor;
an engine including a rotational assembly configured for rotation about a rotational axis of the engine, and the rotational assembly is coupled to the propulsor;
an electrical assembly including an electric motor, an electrical distribution system, and an electrical current sensor, the electric motor is coupled to the propulsor, the electric motor is electrically connected to the electrical distribution system, the electrical current sensor is configured to measure an electrical current supplied to the electric motor by the electrical distribution system; and
a control unit including a processor connected in signal communication with a non-transitory memory including instructions which, when executed by the processor, cause the processor to:
identify a power lever angle of a power throttle for the propulsion system is greater than or less than a power threshold;
identify the electrical current is greater than or less than an electrical current threshold in response to identifying the power lever angle is less than the power threshold; and
disable the electric motor in response to identifying the electrical current is greater than the electrical current threshold.
2 . The propulsion system of claim 1 , wherein the control unit is connected in signal communication with the electric motor, and disabling the electric motor includes commanding the electric motor, with the control unit, to deenergize the electric motor.
3 . The propulsion system of claim 1 , wherein disabling the electric motor includes controlling the electrical distribution system, with the control unit, to electrically isolate the electric motor.
4 . The propulsion system of claim 3 , wherein the electrical distribution system includes a contactor connected in signal communication with the control unit, the contactor is configurable in a closed condition or an open condition, in the closed condition the contactor is configured to supply electrical power to the electric motor from the electrical distribution system, in the open condition the contactor is configured to electrically isolate the electric motor from the electrical distribution system, and controlling the electrical distribution system to electrically isolate the electric motor includes controlling the contactor, with the control unit, from the closed condition to the open condition.
5 . The propulsion system of claim 1 , wherein the electrical assembly includes a battery, and the battery is electrically connected to the electric motor by the electrical distribution system.
6 . The propulsion system of claim 5 , wherein the electrical assembly includes a battery management system for the battery, and the battery management system includes the control unit.
7 . The propulsion system of claim 6 , wherein the battery management system includes a battery sensor assembly for the battery, and the control unit is connected in signal communication with the battery sensor assembly.
8 . The propulsion system of claim 1 , wherein the propulsion system includes a gear box coupling the propulsor to the rotational assembly and the electric motor.
9 . A method for controlling an electric motor of a propulsion system for an aircraft, the method comprising:
driving rotation of a propulsor with an engine of the propulsion system in response to a power lever angle of a power throttle for the propulsion system;
identifying, with a control unit, the power lever angle less than a power threshold;
identifying, with the control unit, an electrical current supplied to an electric motor of the propulsion system from an electrical distribution system is greater than an electrical current threshold in response to identifying the power lever angle is less than the power threshold, and the electric motor is coupled to the propulsor; and
disabling, with the control unit, the electric motor in response to identifying the electrical current is greater than the electrical current threshold.
10 . The method of claim 9 , wherein disabling the electric motor includes commanding the electric motor, with the control unit, to deenergize the electric motor.
11 . The method of claim 9 , wherein disabling the electric motor includes controlling the electrical distribution system, with the control unit, to electrically isolate the electric motor.
12 . The method of claim 11 , wherein the electrical distribution system includes a contactor connected in signal communication with the control unit, the contactor is configurable in a closed condition or an open condition, in the closed condition the contactor is configured to supply electrical power to the electric motor from the electrical distribution system, in the open condition the contactor is configured to electrically isolate the electric motor from the electrical distribution system, and controlling the electrical distribution system to electrically isolate the electric motor includes controlling the contactor, with the control unit, from the closed condition to the open condition.
13 . The method of claim 9 , wherein the steps of identifying the power lever angle is less than the power threshold, identifying the electrical current supplied to the electric motor is greater than the electrical current threshold, and disabling the electric motor are performed while driving rotation of the propulsor with the engine.
14 . The method of claim 9 , wherein the steps of identifying the power lever angle is less than the power threshold, identifying the electrical current supplied to the electric motor is greater than the electrical current threshold, and disabling the electric motor are performed during a landing sequence of the aircraft.
15 . A propulsion system for an aircraft, the propulsion system comprising:
a propulsor;
an engine including a rotational assembly configured for rotation about a rotational axis of the engine, and the rotational assembly is coupled to the propulsor; and
an electrical assembly including an electric motor, an electrical distribution system, a battery, a battery management system, and an electrical current sensor, the electric motor is coupled to the propulsor, the electric motor and the battery are electrically connected to the electrical distribution system, the electrical current sensor is configured to measure an electrical current supplied to the electric motor by the electrical distribution system, the battery management system includes a battery sensor assembly for the battery, and the battery management system further includes a processor connected in signal communication with a non-transitory memory including instructions which, when executed by the processor, cause the processor to:
identify a power lever angle of a power throttle for the propulsion system is greater than or less than a power threshold;
identify the electrical current is greater than or less than an electrical current threshold in response to identifying the power lever angle is less than the power threshold; and
disable the electric motor in response to identifying the electrical current is greater than the electrical current threshold.
16 . The propulsion system of claim 15 , wherein the battery management system is connected in signal communication with the electric motor, and disabling the electric motor includes commanding the electric motor, with the battery management system, to deenergize the electric motor.
17 . The propulsion system of claim 15 , wherein disabling the electric motor includes controlling the electrical distribution system, with the battery management system, to electrically isolate the electric motor.
18 . The propulsion system of claim 17 , wherein the electrical distribution system includes a contactor connected in signal communication with the battery management system, the contactor is configurable in a closed condition or an open condition, in the closed condition the contactor is configured to supply electrical power to the electric motor from the electrical distribution system, in the open condition the contactor is configured to electrically isolate the electric motor from the electrical distribution system, and controlling the electrical distribution system to electrically isolate the electric motor includes controlling the contactor, with the battery management system, from the closed condition to the open condition.
19 . The propulsion system of claim 15 , wherein the propulsion system includes a gear box coupling the propulsor to the rotational assembly and the electric motor.