SYSTEM AND METHOD FOR ACTUATOR MONITORING FOR AN ELECTRIC AIRCRAFT

The system and method for actuator monitoring of an electric aircraft is illustrated. The system includes a plurality of flight components, a computing device attached to each rotor component, and a flight controller. The plurality of flight components are coupled to the electric aircraft. A computing device is communicatively coupled to each rotor component and is configured to detect an input health datum associated with each rotor component of the plurality of flight components and transmit the input health datum to a flight controller. The flight controller is communicatively connected to the computing devices and is configured to receive the health datum from the computing devices, generate an updated health datum as a function of the input health datum, and transmit the updated health datum to each rotor component of the plurality of flight components.