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.

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.

There is described a method and system for operating a hybrid electric aircraft propulsion system. The method comprises modulating AC electric power applied to a first electric propulsor or a second electric propulsor from at least one motor inverter to synchronize the frequency of the first electric propulsor or the second electric propulsor with the frequency of a generator.

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.

A magnetic coupling apparatus, for transmitting drive from a driving member to a driven member, wherein the driving member has at least one first magnet and the driven member has a plurality of second magnets, and wherein the driving member and the driven member are arranged so that, as the driving member rotates, the at least one first magnet approaches one of the second magnets and thus exerts a force upon it which causes the driven member to rotate.

When motor is energised, driving member will rotate and bring a magnet towards a magnet, which will cause driven member to turn. As member reaches operating speed, the repeated repulsive kicks from magnets to magnets will synchronise the rotations. One member carries four magnets and an other member has eight magnets. The member with more magnets will rotate at half the speed of the other member.

A magnetic coupling apparatus, for transmitting drive from a driving member to a driven member, wherein the driving member has at least one first magnet and the driven member has a plurality of second magnets, and wherein the driving member and the driven member are arranged so that, as the driving member rotates, the at least one first magnet approaches one of the second magnets and thus exerts a force upon it which causes the driven member to rotate.

When motor is energised, driving member will rotate and bring a magnet towards a magnet, which will cause driven member to turn. As member reaches operating speed, the repeated repulsive kicks from magnets to magnets will synchronise the rotations. One member carries four magnets and an other member has eight magnets. The member with more magnets will rotate at half the speed of the other member.

An electromechanical converter for automatically adjusting driving torque from an engine of a vehicle comprises a rotor, a stator, and a set of windings. The set of windings comprises main windings, subsidiary windings, and auxiliary windings. The rotor is housed within a stator, comprises a pole. A hub of the stator shaft is engaged to auxiliary stator and transfers energy from the engine to output. Each coil of the main and subsidiary windings is wound on each pole. Each coil of the auxiliary windings is wound between poles. The stator is separated from the rotor by gap. An output shaft is connected to auxiliary stator and it is engaged to the stator shaft. The comparative rotating of the rotor and stator creates current at the windings of the rotor and the stator.

An electromechanical converter for automatically adjusting driving torque from an engine of a vehicle comprises a rotor, a stator, and a set of windings. The set of windings comprises main windings, subsidiary windings, and auxiliary windings. The rotor is housed within a stator, comprises a pole. A hub of the stator shaft is engaged to auxiliary stator and transfers energy from the engine to output. Each coil of the main and subsidiary windings is wound on each pole. Each coil of the auxiliary windings is wound between poles. The stator is separated from the rotor by gap. An output shaft is connected to auxiliary stator and it is engaged to the stator shaft. The comparative rotating of the rotor and stator creates current at the windings of the rotor and the stator.