US-12617539-B2 - Method and system for mitigating an electric motor fault in an aircraft power plant

US12617539B2US 12617539 B2US12617539 B2US 12617539B2US-12617539-B2

Abstract

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.

Inventors

Alireza Gharagozloo
Michael Hanna

Assignees

PRATT & WHITNEY CANADA CORP.

Dates

Publication Date: 20260505
Application Date: 20230623

Claims (15)

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.

Description

TECHNICAL FIELD The disclosure relates generally to aircraft power plants and, more particularly, to mitigating electric motor faults in aircraft power plants. BACKGROUND In an aircraft power plant including electric propulsion, electrical energy is converted to mechanical energy by an electric motor to drive an air mover, such as a fan or a propeller. In case of a fault associated with the electric motor, the electric motor could potentially enter into an over torque condition or an over speed condition, which could negatively affect the operation of the aircraft to which the power plant is mounted. Improvement is desired. SUMMARY In one aspect, the disclosure describes 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 from the power lever; andafter receiving the deactivation request, deactivating the electric motor independently of the controller. The method may include generating the deactivation request in response the power lever being moved to a prescribed power lever position. The prescribed power lever position may be an idle position. Generating the deactivation request may include actuating a switch from movement of the power lever to the prescribed power lever position. The method may include generating the deactivation request in response to an actuation of a manual switch located on the power lever. Disabling the electric motor may include disconnecting the electric motor from a power source configured to power the electric motor. The controller may be a first controller for the electric motor. The method may include: receiving the deactivation request at a second controller for the electric motor; and using the second controller to deactivate the electric motor. The deactivation request may be indicative of a request for zero output torque from the electric motor. The method may include deactivating the electric motor via a communication path that excludes the controller. The method may include: 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. The aircraft power plant may include a thermal engine configured to propel the aircraft. The method may include controlling the thermal engine according to the power request. Embodiments may include combinations of the above features. In another aspect, the disclosure describes a method of operating an aircraft power plant including an electric motor configured to propel an aircraft. The method comprises: 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 from the power lever; anddeactivating 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. The first communication path may include a motor controller. The second communication path may exclude the motor controller. The first communication path may include a first motor controller. The second communication path may include a second motor controller. The power aircraft plant may include a thermal engine configured to propel the aircraft. The method may include controlling the thermal engine according to the power request. Embodiments may include combinations of the above features. In a further aspect, the disclosure describes a system for operating an aircraft power plant including an electric motor configured to propel an aircraft. The system comprises: a power lever configured to be 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; anda switch disposed on said power lever or actuatable by the power lever, the switch being actuatable to generate a deactivation request to deactivate the electric motor independently of the electric motor. The switch may be actuatable via a push button disposed on the power lever. The switch may be actuatable by movement of the power lever to a prescribed lever position. The system may include a contactor configured to disconnect the electric motor from a po