Abstract: An aircraft electromechanical actuator control system for an aircraft having a direct current (DC) voltage bus includes an actuator controller that is coupled to receive a first DC voltage from the aircraft DC voltage bus, where the first DC voltage has a first voltage magnitude. The actuator controller selectively supplies AC voltage to an electromechanical actuator and includes a bidirectional DC/DC converter, an inverter, and actuator control logic. The bidirectional DC/DC converter receives the first DC voltage and supplies a second DC voltage having a second voltage magnitude that is less than the first voltage magnitude. The inverter receives the second DC voltage converts it to the AC voltage. The actuator control logic receives actuator commands and supplies inverter control signals to the inverter.

Abstract: A motor control system includes a multi-phase motor, a multi-phase inverter circuit, a plurality of controllable switches, a plurality of sensors, and a monitor circuit. Each controllable switch is coupled in series between a second terminal of the motor and a common winding node and is responsive to switch commands to operate in either a first switch mode or a second switch mode. The monitor circuit is responsive to sensor signals to determine when one or more of the sensed motor state variables attains a predetermined threshold magnitude and when one or more of the sensed motor state variables attains the predetermined threshold magnitude, to supply a switch command to one or more of the controllable switches that causes the one or more controllable switches to operate in the second switch mode.