1. An electronic brake control system for an aircraft, comprising: a brake control unit; an electronic brake actuation controller electrically coupled to the brake control unit; an electronic brake actuator electrically coupled to the electronic brake actuation controller, the electronic brake actuator comprising a motor, wherein the electronic brake actuator comprises at least one of a first actuator type having a Hall Effect sensor configured to identify an angular position of the motor or a second actuator type having a resolver to identify the angular position of the motor, and wherein the electronic brake actuation controller is configured to detect a type of the electronic brake actuator based on a difference between a voltage drop across a pull-up resistor located within the electronic brake actuator where the electronic brake actuator is of the first actuator type and a voltage drop across a load sensor located within the electronic brake actuator where the electronic brake actuator is of the second actuator type; a sense resistor electrically coupled in series with the electronic brake actuator, wherein the sense resistor is coupled between ground and at least one of the pull-up resistor or an E− terminal of the load sensor, and wherein the sense resistor is located within the electronic brake actuation controller; and a brake assembly of the aircraft in operable communication with the electronic brake actuator.