Method and system for mitigating an electric motor fault in an aircraft power plant
AssigneePratt & Whitney Canada Corp.
InventorsAlireza Gharagozloo, Michael Hanna
Life of this patent
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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.
Claims15
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.
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.
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.
Dependencies are inferred from the claim text.