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 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.

Disclosed is an electric machine and a traction machine utilizing the electric machine. The electric traction chain includes an electric machine, a plurality of power converters configured to generate AC power signals associated with the various phases of the electric machine, and a plurality of DC power sources. The electric machine includes a rotor and a stator, the stator including at least one winding made from coilings of an insulated conductive material, each winding being associated with one phase of the electric machine, and including a plurality of independently powered coils. Each DC power source of the electric machine is associated with a separate power converter, the coils of a same winding are powered by power signals associated with a same phase generated by the separate power converters.

Disclosed is an electric machine and a traction machine utilizing the electric machine. The electric traction chain includes an electric machine, a plurality of power converters configured to generate AC power signals associated with the various phases of the electric machine, and a plurality of DC power sources. The electric machine includes a rotor and a stator, the stator including at least one winding made from coilings of an insulated conductive material, each winding being associated with one phase of the electric machine, and including a plurality of independently powered coils. Each DC power source of the electric machine is associated with a separate power converter, the coils of a same winding are powered by power signals associated with a same phase generated by the separate power converters.

A wind driven electric generator comprises: a fan element including a fan blade and a transmission shaft, the fan blade being served to receive a wind force for rotation, the transmission shaft transferring the rotary motion of the fan blade; a first generator being driven by the transmission shaft to generate electric energy; a motor receiving the electric energy generated by the first generator to rotate the transmission shaft; and a generating device including a second generator, a maximum power point tracker and an energy storage element, the second generator being driven by the transmission shaft to generate electric energy, the electric energy generated by the second generator being stored to the energy storage element under the control of the maximum power point tracker.

A wind driven electric generator comprises: a fan element including a fan blade and a transmission shaft, the fan blade being served to receive a wind force for rotation, the transmission shaft transferring the rotary motion of the fan blade; a first generator being driven by the transmission shaft to generate electric energy; a motor receiving the electric energy generated by the first generator to rotate the transmission shaft; and a generating device including a second generator, a maximum power point tracker and an energy storage element, the second generator being driven by the transmission shaft to generate electric energy, the electric energy generated by the second generator being stored to the energy storage element under the control of the maximum power point tracker.

A generator system, including first and second generators each having an inverter circuit outputting AC, a connection circuit connecting the generators through a power line, a master-slave determining unit determining one of the generators as a master generator, and to determine other of the generators as a slave generator, a data acquiring unit acquiring an output data of the master generator, and a synchronization controlling unit controlling switching operation of the inverter circuit of the slave generator based on the output data of the master generator to synchronize an output data of the slave generator with the output data of the master generator, wherein the master-slave determining unit determines one of the generators that starts earlier as the master generator, and when the generators start simultaneously, to determine one of the generators as the master generator in accordance with a predefined rule.

A generator system, including first and second generators each having an inverter circuit outputting AC, a connection circuit connecting the generators through a power line, a master-slave determining unit determining one of the generators as a master generator, and to determine other of the generators as a slave generator, a data acquiring unit acquiring an output data of the master generator, and a synchronization controlling unit controlling switching operation of the inverter circuit of the slave generator based on the output data of the master generator to synchronize an output data of the slave generator with the output data of the master generator, wherein the master-slave determining unit determines one of the generators that starts earlier as the master generator, and when the generators start simultaneously, to determine one of the generators as the master generator in accordance with a predefined rule.

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.

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.