A power system for a locomotive. The power system includes an alternator, a first inverter system, a traction motor, a second inverter system and an auxiliary power unit. The first inverter system is coupled to the alternator and receives high voltage power from the alternator. The traction motor is coupled to the first inverter system receives high voltage power from the first inverter system. The second inverter system is also coupled to the alternator. The second inverter system steps down the high voltage power from the alternator. The auxiliary power unit is coupled to the second inverter system and receives the stepped down voltage power from the second inverter system.

An electric drive-train for a ship includes a first generator having a rotatable shaft structured to be driven by a first prime mover and an output providing a voltage; a second generator having a rotatable shaft structured to be driven by a second prime mover and an output providing a voltage; an electric machine including a rotatable shaft structured to drive a propeller; a first power electronic converter electrically interconnected with the output of the first generator and structured to power the electric machine; and a second power electronic converter electrically interconnected with the output of the second generator and structured to power the electric machine. A support structure replaces a reduction gear box and supports the first generator, the second generator, the electric machine, the first power electronic converter, and the second power electronic converter.

While coolant is used to cool a motor inverter and a generator inverter included in a power drive unit configured to invert power between a battery and a motor/generator in both directions, an EV travel mode and a power generation travel mode are switched according to detection values from sensors in an electrically driven vehicle and including a switching device temperature sensor for a switching device of the inverters and a coolant temperature sensor, thereby controlling the vehicle. A failure of the coolant temperature sensor is detected according to a detection value from the coolant temperature sensor, and, in the EV travel mode, a detection value detected by the switching device temperature sensor for the switching device of the generator inverter is set as a detection value of a temperature of the coolant when the failure of the coolant temperature sensor is detected.

The invention relates to a turbomachine of an aircraft comprising an outer casing (2) delimiting with an inner hub (3), a flow path (1) of a gas stream in which is disposed a low-pressure turbine configured to rotationally drive a low-pressure shaft; said turbomachine comprising, in the direction of flow of the gas stream, a first propeller (31); and a second propeller (32) downstream of the first propeller, the first propeller (31) being rotationally driven by said low-pressure shaft and the second propeller being rotationally driven by an electric motor (70), the second propeller (32) being further disposed at a distance between 1.5 and 4 cord lengths (LC1) from the first propeller (31) defined between the respective axes of shimming (A31, A32) of each of the first and second propellers.

A method for controlling an actuator system of a motor vehicle includes utilizing a model predictive control (MPC) module with an MPC solver to determine optimal positions of one or more actuators of the actuator system. The method further includes receiving a plurality of actuator system parameters, and triggering the MPC solver to generate one or more control commands from plurality of actuator system parameters. The method further includes applying a cost function to reduce a steady-state tracking error in the one or more control commands from the MPC solver and applying the one or more control commands to alter positions of the one or more actuators, and applying a penalty term to the steady-state predictions of positions of the plurality of actuators to limit a difference between a steady-state prediction of the actuator system and a solution from the MPC solver.

A vehicle control method in a hybrid electric vehicle including an internal combustion engine, a battery, an electric motor, and a control unit. The method includes estimating an estimated vehicle velocity trajectory, estimating an initial engine power trajectory, simulating state of charge of the battery with the vehicle velocity trajectory and the initial engine power trajectory, estimating an initial terminal co-state value, simulating backward co-state dynamics using the state of charge and vehicle velocity trajectory, to obtain a resulting co-state trajectory. The co-state trajectory is used to solve a minimization control and propagate state of charge dynamics forward in time. The method includes updating control and the co-state trajectory, adjusting the terminal co-state value, and controlling a usage of the battery and the internal combustion engine. The method can be performed to optimize the engine power trajectory to minimize fuel consumption in real time.

Lightweight, energy-dense, high-efficiency, hybrid power systems for electric aircraft including a prime mover internal combustion engine or gas turbine coupled to a self-cooling polyphase axial-flux dual-Halbach-array motor/alternator where the number of phases N.sub.phase is greater than or equal to three. The motor/alternator is connected to a regenerative power converter drive also having N.sub.phase phases, which, in turn, is connected to a DC power bus, a battery, a battery management system, and a system controller. In some embodiments, the motor/alternator and regenerative power converter drive have a neutral connection.

Lightweight, energy-dense, high-efficiency, hybrid power systems for electric aircraft including a prime mover internal combustion engine or gas turbine coupled to a self-cooling polyphase axial-flux dual-Halbach-array motor/alternator where the number of phases N.sub.phase is greater than or equal to three. The motor/alternator is connected to a regenerative power converter drive also having N.sub.phase phases, which, in turn, is connected to a DC power bus, a battery, a battery management system, and a system controller. In some embodiments, the motor/alternator and regenerative power converter drive have a neutral connection.

A drive control device includes a self-excited generator to generate and output electric power by being driven by an internal combustion engine, and a separately excited generator to generate and output electric power by being driven by the internal combustion engine when the separately excited generator is in an excited state. The drive control device further includes a first power converter to convert electric power fed from the separately excited generator via primary terminals into DC power and output the DC power via secondary terminals or to convert DC power fed via the secondary terminals into electric power to be fed to the separately excited generator and output the electric power via the primary terminals, and a capacitor connected between the secondary terminals of the first power converter.

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.