An electric drive device includes one shaft extending in a prescribed axial direction, a first rotary electric machine and a second rotary electric machine each arranged coaxially with the shaft and connected to the shaft, a first controller electrically connected to the first rotary electric machine and configured to control driving of the first rotary electric machine, and a second controller electrically connected to the second rotary electric machine and configured to control driving of the second rotary electric machine. The first rotary electric machine and the second rotary electric machine are spaced apart from each other in the axial direction of the shaft, and the first controller and the second controller are arranged between the first rotary electric machine and the second rotary electric machine.

An electric drive device includes one shaft extending in a prescribed axial direction, a first rotary electric machine and a second rotary electric machine each arranged coaxially with the shaft and connected to the shaft, a first controller electrically connected to the first rotary electric machine and configured to control driving of the first rotary electric machine, and a second controller electrically connected to the second rotary electric machine and configured to control driving of the second rotary electric machine. The first rotary electric machine and the second rotary electric machine are spaced apart from each other in the axial direction of the shaft, and the first controller and the second controller are arranged between the first rotary electric machine and the second rotary electric machine.

A power and energy management (PEM) method for managing power consumed by a plurality of power devices on a network. The method includes: a monitoring step (S1) to determine whether PEM is required based on the power available on the network and the power consumption of the power devices on the network; a monitor step (S2) to determine the operating status of each of the power devices on the network; a step (S4) of determining a strategy for operating the power devices in response to a determination in the monitoring step that PEM is required; a step (S5) of determining a coordination strategy for recharging of any storage devices on the network in response to a determination in the first network monitoring step that PEM is not required; and controlling (S6) devices on the network to operate at a power consumption level and/or to recharge based on the above steps.

A power and energy management (PEM) method for managing power consumed by a plurality of power devices on a network. The method includes: a monitoring step (S1) to determine whether PEM is required based on the power available on the network and the power consumption of the power devices on the network; a monitor step (S2) to determine the operating status of each of the power devices on the network; a step (S4) of determining a strategy for operating the power devices in response to a determination in the monitoring step that PEM is required; a step (S5) of determining a coordination strategy for recharging of any storage devices on the network in response to a determination in the first network monitoring step that PEM is not required; and controlling (S6) devices on the network to operate at a power consumption level and/or to recharge based on the above steps.

To provide a fuel cell system configured to charge a battery with maintaining the independence and redundancy of a fuel cell and a battery as power sources. A fuel cell system for air vehicles, wherein the fuel cell system comprises a fuel cell, a battery, a motor and a controller; wherein the fuel cell and the battery are connected to the motor as independent power sources, and the motor includes a double three-phase winding that uses a double inverter; and wherein, when normal output is requested from the motor, the controller operates the motor by a predetermined first output from the fuel cell, and the controller charges the battery by a torque generated in the motor.

A rotational power device including a blade having a core formed by battery material as a power source.

An electric propulsion system includes at least one generator. The electric propulsion system also includes at least one drive engine coupled to the at least one generator. The electric propulsion system further includes at least one electrical device. The electric propulsion system also includes at least one battery integrated isolated power converter (BIIC), where the at least one generator and at least one of the at least one BIIC and the at least one electrical device are coupled, and where the at least one BIIC and the at least one electrical device are coupled.

A multiple energy source management system for an integrated hydrogen-electric engine is disclosed, the system includes a first and a second energy source providing energy to the integrated hydrogen-electric engine. A pre-charge load to provide an energy demand to a selected energy source. A sensor monitoring a power output from the first and/or second energy source. A relay to switch between the first and second energy sources. A computer system to receive an output energy of the first energy source, determine if the output energy is below a threshold value, switch the relay from the first state to the third state for a predetermined period of time, based on the determination, pre-charge the second energy source by the pre-charge load; and switch the relay to the second state after the predetermined period of time.

Embodiments of a propulsion system are provided herein. In some embodiments, a propulsion system for an aircraft may include an electrical power supply; a motor coupled to the electrical power supply, wherein the electrical power supply provides power to the motor; and a fan disposed proximate a rear portion of an aircraft and rotatably coupled to the motor, wherein the fan is driven by the motor.

A solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to rely on free flight control at high altitude and under conventional conditions, thereby providing flight duration in excess of 2 months. The aircraft is particularly suitable for use as part of a telecommunications network. A telecommunications network incorporating such aircraft is also discussed.