Method and system for mitigating an electric motor fault in an aircraft power plant
Methods and systems for operating an aircraft power plant including an electric motor configured to propel an aircraft are provided. The methods and systems are used to mitigate a fault associated with the electric motor. The method includes receiving a power request from a power lever of the aircraft and using a controller to control the electric motor according to the power request. After a fault associated with the electric motor has been detected, the method includes receiving a deactivation request from the power lever. After receiving the deactivation request, the electric motor is deactivated independently of the controller.
1 . A method of operating an aircraft power plant including an electric motor configured to propel an aircraft, the method comprising:
receiving a power request from a power lever of the aircraft;
using a controller to control the electric motor according to the power request;
after a fault associated with the electric motor has been detected, receiving a deactivation request to deactivate the electric motor in response to the power lever being positioned in an idle position; and
after receiving the deactivation request, deactivating the electric motor independently of the controller.
2 . The method of claim 1 , wherein generating the deactivation request includes actuating a switch from movement of the power lever to the idle position.
3 . The method of claim 1 , wherein the deactivating of the electric motor comprises disconnecting the electric motor from a power source configured to power the electric motor.
4 . The method of claim 1 , wherein: the controller is a first controller for the electric motor; and the method further includes: receiving the deactivation request at a second controller for the electric motor; and using the second controller to deactivate the electric motor.
5 . The method of claim 4 , wherein the deactivation request is indicative of a request for zero output torque from the electric motor.
6 . The method of claim 1 , further comprising deactivating the electric motor via a communication path that excludes the controller.
7 . The method of claim 1 , further comprising:
using a first communication path between the power lever and the electric motor to control the electric motor according to the power request, the first communication path including the controller; and
using a second communication path between the power lever and the electric motor to deactivate the electric motor, the second communication path being separate from the first communication path.
8 . The method of claim 1 , wherein: the aircraft power plant further includes a thermal engine configured to propel the aircraft; and the method includes controlling the thermal engine according to the power request.
9 . A method of operating an aircraft power plant including an electric motor to propel an aircraft, the method comprising:
receiving a power request from a power lever of the aircraft;
controlling the electric motor according to the power request via a first communication path between the power lever and the electric motor;
after a fault associated with the electric motor has been detected, receiving a deactivation request to deactivate the electric motor in response to the power lever being positioned in an idle position; and
deactivating the electric motor via a second communication path between the power lever and the electric motor, the second communication path being separate from the first communication path.
10 . The method of claim 9 , wherein:
the first communication path includes a motor controller; and
the second communication path excludes the motor controller.
11 . The method of claim 9 , wherein:
the first communication path includes a first motor controller; and
the second communication path includes a second motor controller.
12 . The method of claim 9 , wherein: the power aircraft plant further includes a thermal engine to propel the aircraft; and the method further includes controlling the thermal engine according to the power request.
13 . A system for operating an aircraft power plant including an electric motor configured to propel an aircraft, the system comprising:
a power lever actuated by a pilot of the aircraft to generate a power request corresponding to a position of the power lever;
a controller operatively connected to the power lever and configured to control the electric motor according to the power request; and
a switch actuated by movement of the power lever to an idle position, the switch being actuated to generate a deactivation request to deactivate the electric motor independently of the controller when the power lever is positioned at the idle position.
14 . The system of claim 13 , comprising a contactor configured to disconnect the electric motor from a power source configured to power the electric motor, the switch being operatively connected to the contactor via a communication path that excludes the controller.
15 . The system of claim 13 , wherein:
the controller is a first controller for the electric motor; and
the system includes a second controller for the electric motor configured to receive the deactivation request and deactivate the electric motor.