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. 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 double-fed oscillating linear alternator is provided that includes two concentric Halbach type arrays, one stationary and one movable, that do not require magnets or iron laminations to create a strong magnetic field between the two arrays where the movable array oscillates in a linear motion with respect to the stationary array. The two arrays are manufactured from magnet-less and iron-less conductive material using additive manufacturing techniques.

A method to provide control for an alternating current generator. The method includes controlling the alternating current generator by modulating a three-phase wound rotor to counter-rotate the magnetic field relative to a shaft rotation, or alternatively to become synchronous to the shaft rotation. The three-phase wound rotor controls a frequency and a voltage of the alternating current generator.

Systems and methods are provided for braking a translator of a linear multiphase electromagnetic machine. The system detects a fault event, and in response to detecting the fault event, causes the translator to brake using an electromagnetic technique. Braking includes causing the translator to stop reciprocating, by applying a force opposing an axial motion, which may occur within one cycle, or over many cycles. The fault event may include, for example, a fault associated with an encoder, a controller, an electrical component, a communications link, a phase, or a subsystem. The system includes a power electronics system configured to apply current to the phases. The system may use position information, current information, operating parameters, or a combination thereof to brake. Alternatively, the system need not use position information, current information, and operating parameters, and may brake the translator independent of such information.

A dual-voltage brushless motor (30) includes a casing, a motor shaft (20) rotatably coupled to the casing, a rotor fixedly connected to the motor shaft (20), and a stator (28) configured to face the motor. The rotor contains a plurality of permanent magnets, and the stator (28) includes a first set of winding and a second set of winding. The first winding is electrically isolated from the second winding. The dual-voltage brushless motor (30) is adapted to be driven when the first set of winding receives a first control signal or when the second set of winding receives a second control signal. By configuring two separate motor controllers of the motor, the motor (30) can be operated under different power supplies such as AC power supply and DC power supply. As a result the application of the motor is greatly extended.

The invention relates to electric drive apparatuses used in different industries for different applications more particularly to a method for configuration of an electric drive apparatus. The method comprises: receiving in a second apparatus from a first apparatus, said first apparatus having a connection with an at least one electric drive apparatus in a local site, a configuration parameter setting of a first electric drive apparatus of said at least one electric drive apparatus, converting by said second apparatus a second configuration parameter setting from a first configuration parameter setting, said second configuration parameter setting being converted to be compatible with a second electric drive apparatus of said at least one electric drive apparatus, and forwarding by said second apparatus said second configuration parameter setting to said first apparatus, said first apparatus preferably further forwarding said second configuration parameter setting to said second electric drive apparatus.