A motor control apparatus receives a DC power source through a DC terminal and is coupled to a motor. The motor control apparatus includes a brake, an inverter, and a controller. The brake is coupled to the inverter. The brake includes an energy-consuming component and a switch component. The controller controls the inverter to convert the DC power source to drive the motor. When the controller determines that the DC power source is interrupted, the controller stops controlling the inverter, and the switch component is self-driven turned on so that a back electromotive force generated by the motor is consumed through the energy-consuming component.

The present invention relates to control electronics, preferably for an electromechanical actuator, preferably for use in a primary flight control system of an aircraft, wherein the control electronics can connect or connects an electric motor, preferably of the electromechanical actuator, to an electrical or electronic load and/or wherein the control electronics can deactivate or deactivates a DC/DC converter supplying electrical power to the electric motor, and to an electromechanical actuator and to a method for damping the movement of an electromechanical actuator.

A motor drive control device capable of determining a drive state of a motor is provided. The motor drive control device includes a plurality of motor drive circuits performing, based on drive control signals (Sca1 and Sca2) for controlling the number of rotations of a motor, control of energization of the motor and outputting FG signals (fg1 and fg2) having a cycle corresponding to the actual number of rotations of the motor, a composite signal generation circuit receiving an input of each of the FG signals output from the motor drive circuits and generating a composite signal by combining input signals, and a drive control circuit generating, based on a speed command signal indicating a target number of rotations of the motor, the drive control signals and outputting the drive control signals to each of the motor drive circuits. The FG signals output from the motor drive circuits have a phase difference from each other.

A hybrid electric aircraft propulsion system and method of operation are described. The system comprises a thermal engine, a generator coupled to the thermal engine, a first electric propulsor operatively connected to the generator to receive alternating current (AC) electric power therefrom, a second electric propulsor, a generator inverter operatively connected to the generator to convert AC electric power to direct current (DC) electric power, and a first motor inverter operatively connected to the generator inverter and selectively connected to one of the first electric propulsor and the second electric propulsor and configured to receive the DC electric power and provide the first electric propulsor and the second electric propulsor with AC electric power, respectively.

Power supply hold-up time is increased using regenerative braking. A power line disturbance (“PLD”) event is detected in a power supply unit. One or more fan motors associated with the power supply unit may be signaled to provide regenerative braking based on identifying the PLD event, where the one or more fan motors transition from a motor operating mode to a regenerative braking mode. The regenerative braking may be applied to the one or more fan motors associated with the power supply unit, where a hold-up time is extended to prevent shut down of the power supply unit.

A motor actuator of the present invention includes, between a battery and an inverter, a first solid state relay and a second solid state relay in which directions of parasitic diodes are opposite to each other. When supply of power from the battery to the inverter is to be interrupted, the first solid state relay is brought into an OFF state or all of a plurality of field effect transistors are brought into the OFF state, and then the second solid state relay is brought into the OFF state.

A motor control system and a vehicle reliably perform a three-phase active short circuit on a motor when a single-point power source fails. The motor control system includes a bus capacitor and a motor. The motor is connected to a positive direct current bus and a negative direct current bus through three phases of inverter bridges, the positive direct current bus and the negative direct current bus are respectively connected to a positive terminal and a negative terminal of the bus capacitor, and each phase of inverter bridge includes an upper bridge arm connected to the positive direct current bus and a lower bridge arm connected to the negative direct current bus. In addition, the motor control system further includes: an upper gate drive circuit, a lower gate drive circuit, a first power supply unit, and a second power supply unit.

A motor control apparatus receives a DC power source through a DC terminal and is coupled to a motor. The motor control apparatus includes a brake, an inverter, and a controller. The brake is coupled to the inverter. The brake includes an energy-consuming component and a switch component. The controller controls the inverter to convert the DC power source to drive the motor. When the controller determines that the DC power source is interrupted, the controller stops controlling the inverter, and the switch component is self-driven turned on so that a back electromotive force generated by the motor is consumed through the energy-consuming component.

A device for speed-dependent braking torque control for electrical machines excited by permanent magnets includes a switching device deliberately short-circuits the electrical machine. The switching device is controlled as a function of an induced voltage generated by the electrical machine. If the induced voltage falls below a defined value, the switching device reverses the short-circuited state of the electrical machine to cause the braking torque to reduce to zero and the speed to increase again. The speed can thus be controlled within a range by alternately opening and closing the switching device.

A vehicle is provided that includes a basic structure; and coupled to the basic structure, power sources, a propulsion system and power distribution circuitry. The propulsion system includes a plurality of electric motors configured to power propulsors to generate propulsive forces that cause the vehicle to move. The power distribution circuitry is configured to deliver DC electric power from the power sources to the electric motors, the power distribution circuitry including a plurality of DC-to-DC converter assemblies configured to input the DC electric power from the power sources and deliver voltage-regulated outputs to the electric motors, a DC-to-DC converter assembly operatively coupled to multiple ones of the power sources and multiple ones of the electric motors, and the DC-to-DC converter assembly including a multiple-input and multiple-output (MIMO) transformer with a single transformer core.