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.

An electric system of an electromechanical power transmission chain is provided that includes a first capacitive circuit, converter equipment between the first capacitive circuit and an electric machine, a second capacitive circuit, and a direct voltage converter between the first and second capacitive circuits. The electromechanical power transmission chain is a parallel transmission chain where the electric machine is mechanically connected to a combustion engine and to one or more actuators. The electric system includes a control system for controlling the direct voltage converter in response to changes in a first direct voltage of the first capacitive circuit and for controlling the converter equipment in response to changes in a second direct voltage of the second capacitive circuit. The first direct voltage is kept on a predetermined voltage range whereas the second direct voltage is allowed to fluctuate in order to respond to peak power needs.

An electric system of an electromechanical power transmission chain is provided that includes a first capacitive circuit, converter equipment between the first capacitive circuit and an electric machine, a second capacitive circuit, and a direct voltage converter between the first and second capacitive circuits. The electromechanical power transmission chain is a parallel transmission chain where the electric machine is mechanically connected to a combustion engine and to one or more actuators. The electric system includes a control system for controlling the direct voltage converter in response to changes in a first direct voltage of the first capacitive circuit and for controlling the converter equipment in response to changes in a second direct voltage of the second capacitive circuit. The first direct voltage is kept on a predetermined voltage range whereas the second direct voltage is allowed to fluctuate in order to respond to peak power needs.

An electric system of an electromechanical power transmission chain is provided that includes a first capacitive circuit, converter equipment between the first capacitive circuit and one or more electric machines, a second capacitive circuit, and a direct voltage converter between the first and second capacitive circuits. The electric system includes a control system for controlling the direct voltage converter in response to changes in first direct voltage of the first capacitive circuit and for controlling the converter equipment in response to changes in second direct voltage of the second capacitive circuit. The control of the first direct voltage is faster than the control of the second direct voltage so as to keep the first direct voltage on a predetermined voltage range and to allow the second direct voltage to fluctuate in order to respond to peak power needs.

An electric system of an electromechanical power transmission chain is provided that includes a first capacitive circuit, converter equipment between the first capacitive circuit and one or more electric machines, a second capacitive circuit, and a direct voltage converter between the first and second capacitive circuits. The electric system includes a control system for controlling the direct voltage converter in response to changes in first direct voltage of the first capacitive circuit and for controlling the converter equipment in response to changes in second direct voltage of the second capacitive circuit. The control of the first direct voltage is faster than the control of the second direct voltage so as to keep the first direct voltage on a predetermined voltage range and to allow the second direct voltage to fluctuate in order to respond to peak power needs.

There is provided a hybrid electric aircraft propulsion system and method for operating same. The method comprises providing, to a first electric motor and a second electric motor, alternating current (AC) electric power from a generator, the generator receiving rotational power from a thermal engine, providing, to the first electric motor and the second electric motor, AC electric power from at least one motor inverter, the at least one motor inverter configured to convert DC electric power from a DC power source into AC electric power, and selectively driving the first and second electric motors from the generator, the at least one motor inverter, or a combination thereof, wherein the first electric motor drives a first rotating propulsor and the second electric motor drives a second rotating propulsor.

An aircraft comprising a hybrid electric aircraft propulsion system. The system comprises a first sub-assembly having a first electric propulsor assembly and a first thermal propulsor assembly, the first thermal propulsor assembly having a first thermal engine, a first generator and a first rotating propulsor, the first electric propulsor assembly attached to the aircraft at a first location and the first thermal propulsor assembly attached to the aircraft at a second location. The system also comprises a second sub-assembly having a second electric propulsor assembly and a second thermal propulsor assembly, the second thermal propulsor assembly having a second thermal engine, a second generator and a second rotating propulsor, the second electric propulsor assembly attached to the aircraft at a third location and the second thermal propulsor assembly attached to the aircraft at a fourth location.

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.