Systems and methods are provided for braking a translator of a linear multiphase electromagnetic machine. The system detects a fault event. A polarity indicative of an electromotive force in determined in at least one phase of the linear multiphase electromagnetic machine caused by a motion of the translator. In response to detecting the fault event, the system causes, based on the polarity, a current to be applied to a respective phase of the at least one phase to cause a force acting on the translator that opposes an axial motion of the translator to cause the translator to brake. Braking includes causing the translator to reciprocate at a reduced velocity by opposing axial motion over one or more cycles. The system may use one or more of position information, current information, operating parameters, to brake, or may brake the translator independent of such information.

There is described a method and system for operating a hybrid electric aircraft propulsion system. The method comprises modulating AC electric power applied to a first electric propulsor or a second electric propulsor from at least one motor inverter to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of a generator.

A system includes multiple hybrid energy storage modules (HESMs) configured to accept constant-current DC input power from a main power source. Each HESM has a plurality of outputs configured to sequentially or simultaneously provide both constant-current and constant-voltage output power to multiple loads, the loads comprising steady state, pulsating, or intermittent loads. Each HESM comprises a combined rotating electrical machine-inertial storage module and electro-chemical storage module configured to generate second power that augments or induces first power derived from the main power source, so as to permit constant power draw or constant current draw from the main power source, wherein the output power comprises the first power and the second power.

A motor circuit for driving a motor having two independent sets of windings forming 3 or more phases, wherein each phase of a first set is paired with a respective phase of a second set. A first bridge driver circuit has a top side switch and a bottom side switch driving each phase of the first set, and a second bridge driver circuit has a top side switch and a bottom side switch driving each phase of the second set. First and second current determining means determine current flowing in each respective sets of windings independent of the current flowing in the other set of phase windings. A third current determining means is configured to determine the sum of the current flowing in each pair of the N pairs of phases of the motor.

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.

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.

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.

Two inverters provided at respective both ends of open-end windings are appropriately controlled. A rotating electrical machine control device (1) that can control a first inverter (11) and a second inverter (12) by a plurality of control schemes, respectively, the control schemes differing from each other in at least one of a switching pattern and a switching frequency and being independent of each other, has a control mode in which the first inverter (11) and the second inverter (12) are controlled by the same control scheme in a first speed region (VR1) in which the rotational speed of a rotating electrical machine (80), and the first inverter (11) and the second inverter (12) are controlled by different control schemes in a second speed region (VR2) in which the rotational speed of the rotating electrical machine (80) is higher than in the first speed region (VR1).

For starting an AC electric motor of a mining vehicle, it is first accelerated to a first speed with a second AC voltage provided by an onboard battery-powered inverter of the mining vehicle. A phase of a first AC voltage taken from an external grid is compared to a phase of said second AC voltage. If the phase difference between the first and second AC voltages is larger than a predetermined limit, the speed at which said inverter rotates said AC electric motor is changed. If the difference between the phases of the first and second AC voltages is smaller than the predetermined limit, a change is made from rotating the AC electric motor with the second AC voltage to rotating the AC electric motor with the first AC voltage.

A control device according to the present invention is provided with a data acquisition unit configured to acquire data on at least an operating state of an industrial machine, a learning model storage unit configured to store a learning model in which the value of a setting action for a base speed of a servomotor for peak cut is associated with the operating state of the industrial machine, and a decision making unit configured to settle the setting action for the base speed of the servomotor for peak cut based on the data on the operating state of the industrial machine acquired by the data acquisition unit, by using the learning model stored in the learning model storage unit.