Methods and apparatus for detecting and characterizing arc faults in an aerospace electric propulsion system and then coordinating the operation of various elements of the protection system to execute a fault-clearing sequence. In a current-based method, the arc is detected and characterized based on differential readouts from current sensors. The difference between currents measured at two ends of a protection zone are compared to a difference threshold. In a power-based method, the arc is detected and characterized based on differential readouts from voltage and current sensors. The differential voltage and current readouts are used to compute the respective powers at two ends of a protection zone. The difference between the respective powers is integrated over a period of time and then the integrated difference is compared to a difference threshold. A differential protection trip mode is invoked when the difference threshold is exceeded.
Protection system for aircraft electric propulsion motor and motor controller
2024-01-23
Patent
Electronic Resource
English
Protection System for Aircraft Electric Propulsion Motor and Motor Controller
European Patent Office | 2022
|PROTECTION SYSTEM FOR AIRCRAFT ELECTRIC PROPULSION MOTOR AND MOTOR CONTROLLER
European Patent Office | 2022
|PROTECTION SYSTEM FOR AIRCRAFT ELECTRIC PROPULSION MOTOR AND MOTOR CONTROLLER
European Patent Office | 2022
|PROTECTION SYSTEM FOR AIRCRAFT ELECTRIC PROPULSION MOTOR AND MOTOR CONTROLLER
European Patent Office | 2022
|Protection system for aircraft electric propulsion motor and motor controller
European Patent Office | 2022
|