An electric power supply is disclosed having high-voltage, direct-current (HVDC) circuitry comprising one or more DC pre-charge capacitors and one or more power transistor switches, the HVDC circuitry configured to receive high-voltage, direct-current (HVDC) input power of about 320 volts and/or greater and convert the HVDC input power to multi-phase, high-voltage, alternating-current (HVAC) output power of about 320 volts and/or greater; and low-voltage, direct current (LVDC) circuitry adapted and configured to operate on low-voltage, direct-current, wherein the LVDC circuitry is configured to control and monitor the multi-phase HVAC output power. The electric power supply is further configured to operate in reverse and convert received multiphase HVAC input power to HVDC output power.

An electric power supply is disclosed having high-voltage, direct-current (HVDC) circuitry comprising one or more DC pre-charge capacitors and one or more power transistor switches, the HVDC circuitry configured to receive high-voltage, direct-current (HVDC) input power of about 320 volts and/or greater and convert the HVDC input power to multi-phase, high-voltage, alternating-current (HVAC) output power of about 320 volts and/or greater; and low-voltage, direct current (LVDC) circuitry adapted and configured to operate on low-voltage, direct-current, wherein the LVDC circuitry is configured to control and monitor the multi-phase HVAC output power. The electric power supply is further configured to operate in reverse and convert received multiphase HVAC input power to HVDC output power.

A superconducting flux barrier electric motor, including at least one induced element and at least one conductor, one of the armature or the inductor housing at least one rotor and at least one superconducting induction coil, and the other including at least one arrangement of the electromagnetic coils coaxial with the superconducting induction coil the rotor comprising superconducting pellets mounted radially inside the superconducting coil on an axis of rotation of the motor, where the electromagnetic coils are made of superconducting material and the induced element and the inductor are arranged in an assembly forming a cooling chamber provided with specific cooling means for the superconducting elements of the induced element and the inductor.

An aircraft heat exchanger system according to an exemplary embodiment of this disclosure, among other possible things includes a first heat exchanger assembly that is disposed in an inlet duct assembly, and a skin heat exchanger assembly is in thermal communication with an outer surface of an aircraft structure. The skin heat exchanger is in fluid communication with the first heat exchanger such that a working fluid is communicated therebetween.

An aircraft heat exchanger system according to an exemplary embodiment of this disclosure, among other possible things includes a first heat exchanger assembly that is disposed in an inlet duct assembly, and a skin heat exchanger assembly is in thermal communication with an outer surface of an aircraft structure. The skin heat exchanger is in fluid communication with the first heat exchanger such that a working fluid is communicated therebetween.

An arrangement for cooling at least one power module of a power converter is disclosed herein. The arrangement includes power semiconductor components. The power module is arranged in a drive flow of an engine in such a way that the drive flow flows around cooling ribs of the power module. The disclosure also relates to a power converter, (e.g., an inverter), including an arrangement of this kind and an aircraft, (e.g., an airplane), including a power converter of this kind.

An arrangement for cooling at least one power module of a power converter is disclosed herein. The arrangement includes power semiconductor components. The power module is arranged in a drive flow of an engine in such a way that the drive flow flows around cooling ribs of the power module. The disclosure also relates to a power converter, (e.g., an inverter), including an arrangement of this kind and an aircraft, (e.g., an airplane), including a power converter of this kind.

One embodiment is an electric drive system including a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto via a swashplate; a gear box associated with the plurality of redundant motors; a cyclic actuation system for controlling an individual pitch of the rotor blades connected to the swashplate; and at least one structural element for retaining the redundant motors, the gear box, and the cyclic actuation system together as a single integrated unit.

One embodiment is an electric drive system including a plurality of redundant motors, wherein power generated by the plurality of motors is used to drive a rotor system comprising a rotor shaft having a plurality of rotor blades connected thereto via a swashplate; a gear box associated with the plurality of redundant motors; a cyclic actuation system for controlling an individual pitch of the rotor blades connected to the swashplate; and at least one structural element for retaining the redundant motors, the gear box, and the cyclic actuation system together as a single integrated unit.

An assembly is provided for an aircraft propulsion system. This assembly includes an exhaust center body and a duct system. The exhaust center body includes an exterior skin. The duct system is fluidly coupled with a plurality of exterior skin perforations in the exterior skin. The duct system is configured to direct bypass air received from a bypass flow path within the aircraft propulsion system to the exterior skin perforations.