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.

An electrical power system for a watercraft including a first electrical power plant configured to operate in a variable frequency mode to output variable frequency power to a first electrical network and a fixed frequency mode to output fixed frequency power to a second electrical network. There is a first electrical load including a first high temperature superconductor (HTS) motor connected to the first electrical network and a second electrical load connected to a second electrical network. A controller selectively connects the first electrical power plant to the first electrical network and operates the first electrical power plant in a variable frequency mode to output variable frequency power to power the first HTS motor and selectively connects the first electrical power plant to the second electrical network and operates the first electrical power plant in a fixed frequency mode to output fixed frequency power to power the second electrical load.

An electrical power system for a watercraft including a first electrical power plant configured to operate in a variable frequency mode to output variable frequency power to a first electrical network and a fixed frequency mode to output fixed frequency power to a second electrical network. There is a first electrical load including a first high temperature superconductor (HTS) motor connected to the first electrical network and a second electrical load connected to a second electrical network. A controller selectively connects the first electrical power plant to the first electrical network and operates the first electrical power plant in a variable frequency mode to output variable frequency power to power the first HTS motor and selectively connects the first electrical power plant to the second electrical network and operates the first electrical power plant in a fixed frequency mode to output fixed frequency power to power the second electrical load.

An engine control device for an electric vehicle having an electrical rotating machine, includes: an engine control unit determining an engine rotational speed and an engine torque such that a particulate number of particulate matter per unit gas quantity that the engine releases into an atmosphere becomes equal to or less than a target value having been set in association with a warm-up state of the engine, the engine rotational speed, and the engine torque, and such that the engine rotational speed when a vehicle speed is less than a threshold value is lower than the engine rotational speed when the vehicle speed is equal to or more than the threshold value, and controlling the engine based on the determined engine rotational speed and the engine torque.

An engine control device for an electric vehicle having an electrical rotating machine, includes: an engine control unit determining an engine rotational speed and an engine torque such that a particulate number of particulate matter per unit gas quantity that the engine releases into an atmosphere becomes equal to or less than a target value having been set in association with a warm-up state of the engine, the engine rotational speed, and the engine torque, and such that the engine rotational speed when a vehicle speed is less than a threshold value is lower than the engine rotational speed when the vehicle speed is equal to or more than the threshold value, and controlling the engine based on the determined engine rotational speed and the engine torque.

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 space launch system and method through electromagnetic pushing. The space launch system comprises an energy storage subsystem, an energy conversion subsystem, a linear motor subsystem, and a control maintenance subsystem. The space launch system converts the electric energy into an electromagnetic force. Through the electromagnetic force, a rocket is pushed to be accelerated to a certain speed along an electromagnetic launching track to realize the launching of the rocket.

An electric power system for a vehicle includes at least one electric machine, one or more power rectifiers, and a plurality of DC channels. The at least one electric machine includes a plurality of tooth-wound multi-phase windings that are substantially magnetically decoupled, and the at least one electric machine is mechanically balanced even if one of the plurality of windings is de-energized. The one or more power rectifiers are configured to produce rectified power from the power generated by the at least one electric machine. The plurality of DC channels are formed after the at least one power rectifier and are configured to provide DC power to one or more loads within a vehicle.

A power generation system includes a shroud that defines a fluid flow path. A gas turbine engine is in the fluid flow path, and the gas turbine engine includes a compressor, a combustor downstream from the compressor, and a turbine downstream from the combustor. An electric generator is in the fluid flow path upstream from the compressor. The electric generator includes a rotor coaxially aligned with the turbine, and the turbine and the rotor rotate at the same speed