Two sets of independent armature windings and two sets of control units are provided; a single power-source connector branches into at least four lines in the vicinity of a power-source terminal; a power source relay, a filter, and an inverter circuit are connected, in that order, with a line where a large current flows; a control circuit unit is connected with a line where a small current flows and a detection circuit for detecting an abnormality in the control circuit unit is provided in that line.

A discharge control device performs discharging of a capacitor, in a state in which a battery is not connected to an inverter that drives a motor, by causing electric charges accumulated in the capacitor connected to the inverter to be consumed by windings of the motor. The discharge control device performs the discharging of the capacitor by sequentially generating command values for voltages applied to a axis and a axis while causing a voltage phase in an stationary coordinate system having a rotation axis of a rotor of the motor as an origin and defined by the axis and the axis orthogonal to each other to be inverted in a predefined period.

A method for determining an interrupted motor phase of an electric motor having at least three windings by means of a control unit is disclosed, wherein voltages induced in the windings are determined on outer conductors of the electric motor by means of at least one measuring unit, wherein the measuring unit is connected to at least one outer conductor of the electric motor via at least one resistor, the induced voltages of the outer conductors of the electric motor are compared with one another, and an interrupted motor phase is registered if the induced voltage differs or if a frequency of the induced voltage differs. A control unit, a computer program and a machine-readable storage medium are also disclosed.

An intelligent power module and a controller for an air conditioner are provided. For the intelligent power module, an adjust circuit is additionally provided between a respective drive circuit and a respective IGBT transistor. The adjust circuit detects a change in the voltage of a low voltage power supply of the intelligent power module in real time, and disables the output of the module when the voltage is detected to be too low due to fluctuation of the low voltage power supply. This operation releases the charge accumulated in the IGBT transistor, when energy storage of a drive motor causes charge accumulation of the IGBT transistor. The adjust circuit can continue releasing the charge when the low voltage power supply is restored to normal, to prevent the operating reliability of the module from being affected by the impact of the charge on internal circuits of the module.

A machine tool controller capable of identifying the factors of a warning easily is provided. A controller of a machine tool includes a power supply monitoring unit, a power supply abnormality detecting unit, and an abnormality diagnosis unit. The power supply monitoring unit acquires measurements indicating an operating state of a machine tool and/or a peripheral device (for example, an AC power supply or a motor) of the machine tool. The power supply abnormality detecting unit detects an abnormality in the operating state of the machine tool and/or the peripheral device and outputs a signal indicating the abnormality and the measurements obtained when the abnormality was detected. The abnormality diagnosis unit automatically selects a measurement related to the abnormality among the measurements and automatically diagnoses factors of the abnormality.

An electric vehicle includes drive systems, a control apparatus that controls the drive systems, and wheels. Each drive system includes a motor and an inverter coupled by wires. The wires of the drive systems are coupled by first bypass lines. Each inverter converts direct current power supplied from a corresponding power supply into alternating current power and supplies the alternating current power to the corresponding motor. Each motor drives the corresponding wheel. When an abnormality occurs in the supply of the alternating current power from the inverter to the motor in one drive system, the control apparatus performs control (i) to stop the supply of the alternating current power from the inverter of the one drive systems, and (ii) to supply the alternating current power supplied from the inverter to the motor in another drive system, to the motor of the one drive system via the first bypass lines.

There is provided a hybrid electric aircraft propulsion system and method for operating same. The method comprises providing, to a first electric motor and a second electric motor, alternating current (AC) electric power from a generator, the generator receiving rotational power from a thermal engine, providing, to the first electric motor and the second electric motor, AC electric power from at least one motor inverter, the at least one motor inverter configured to convert DC electric power from a DC power source into AC electric power, and selectively driving the first and second electric motors from the generator, the at least one motor inverter, or a combination thereof, wherein the first electric motor drives a first rotating propulsor and the second electric motor drives a second rotating propulsor.

An aircraft comprising a hybrid electric aircraft propulsion system. The system comprises a first sub-assembly having a first electric propulsor assembly and a first thermal propulsor assembly, the first thermal propulsor assembly having a first thermal engine, a first generator and a first rotating propulsor, the first electric propulsor assembly attached to the aircraft at a first location and the first thermal propulsor assembly attached to the aircraft at a second location. The system also comprises a second sub-assembly having a second electric propulsor assembly and a second thermal propulsor assembly, the second thermal propulsor assembly having a second thermal engine, a second generator and a second rotating propulsor, the second electric propulsor assembly attached to the aircraft at a third location and the second thermal propulsor assembly attached to the aircraft at a fourth location.

Methods and systems for operating a hybrid electric aircraft propulsion system mounted to an aircraft. The method comprises driving a first rotating propulsor from a first electric motor operatively connected to a generator, driving a second rotating propulsor from a second electric motor operatively connected to the generator, and driving a third rotating propulsor from a thermal engine, the thermal engine operatively connected to the generator and configured to drive the generator.

Methods and systems for operating a hybrid electric aircraft propulsion system. The method comprises providing alternating current (AC) electric power to a first electric motor to drive a first rotating propulsor, providing the first electric motor with AC electric power from at least one motor inverter operatively coupled to a direct current (DC) power source, detecting a failure in a path to the first electric motor, and selectively rearranging a first switching arrangement between the generator, the at least one motor inverter, and the first electric motor.