Described are aircraft passenger seat assemblies with a passenger seat, a component with an outer surface attached the passenger seat. An inductive wireless power unit with a coil assembly is included with the aircraft passenger seat assembly, and the coil assembly is positioned within the component. A portion of the outer surface of the component covers the coil assembly. Wires connecting the coil assembly to a power supply are hidden from view within the aircraft passenger seat assembly.

An electrical architecture of an aircraft includes a plurality of primary generators each associated with a propulsion engine of the aircraft, a plurality of primary electrical networks each associated with a primary generator in nominal operating mode, a single-part secondary electrical network, an electrical energy accumulation device connected directly to the secondary network, a first electrical energy converter arranged between the secondary electrical network and a first of the primary electrical networks, allowing energy to be transferred from the first of the primary electrical networks to the secondary electrical network, the first electrical energy converter being intended to supply electrical energy to the electrical energy accumulation device in nominal operating mode, a second electrical energy converter arranged between the secondary electrical network and a second of the primary electrical networks, allowing energy to be transferred from the secondary electrical network to the second of the primary electrical networks.

Provided is a system including: a management unit configured to manage a plurality of battery packs connected in parallel, in which the management unit is configured to control the plurality of battery packs to cause the plurality of battery packs to be discharged alternately so that a discharge rate of each of the plurality of battery packs becomes higher than the discharge rate in a case of discharging all of the plurality of battery packs. The plurality of battery packs include a plurality of left-hand side battery packs and a plurality of right-hand side battery packs, and the management unit is configured to manage the plurality of battery packs to cause at least one of the plurality of battery packs in each of the plurality of left-hand side battery packs and the plurality of right-hand side battery packs to be discharged at a time in order.

A wireless power receiver coil is attached to a landing gear of a drone. The wireless power receiver coil is closer to the drone when the landing gear is in a retracted position and farther away from the drone when the landing gear is in an extended position. A length of the wireless power receiver coil may be the same length when the landing gear is in the retracted position and in the extended position. The wireless power receiver coil may be in a first orientation when the landing gear is in the retracted position and the wireless power receiver coil may be in a different orientation when the landing gear is in the extended position. The wireless power receiver coil may have a first shape when the landing gear is in the retracted position and may have a second shape when the landing gear is in the extended position.

Examples described herein provide a computer-implemented method that includes providing the hybrid electric engine, the hybrid electric engine having a gas generating core and an electric machine powered by electric energy. The method further includes determining, by a processing device, whether a use of the electric energy will increase time on wing of the hybrid electric engine of the aircraft a threshold amount. The method further includes, responsive to determining that the use of energy will increase time on wing the threshold amount, apportioning the electric energy from a battery system of the aircraft to increase the time on wing.

An airport ground power unit for supplying electric current to an aircraft parked on the ground, a method of operating the ground power unit, a system for supplying electric current to an aircraft parked on the ground, a method of operating such system, and a Y-adaptor.

A drive system comprises a DC-DC converter that is arranged to receive an input voltage from a battery having a nominal battery voltage. The DC-DC converter has a first mode of operation in which the DC-DC converter generates a regulated output voltage from the input voltage and supplies the regulated output voltage to a load, and a second mode of operation in which the DC-DC converter is by-passed such that the input voltage from the battery is supplied to the load. A controller is arranged to compare the input voltage to a threshold voltage that is less than the nominal battery voltage. The controller operates the DC-DC converter in the first mode when the input voltage is less than the threshold voltage, and operates the DC-DC converter otherwise.

In an aspect, a system for recharging an electric vehicle. A system includes an electric vehicle. An electric vehicle includes at least a propulsor. An electric vehicle includes a recharging connector electrically connected to a power source. An electric vehicle includes a power storage unit. A power storage unit is configured to store power. An electric vehicle includes a power supply circuit. A power supply circuit is in electric communication with a power storage unit and recharging connector. A power supply circuit includes a buck-boost regulator. A buck-boost regulator includes at least an inductor. A buck-boost regulator includes a switching device to supply intermittent current to at least an inductor. At least one of at least an inductor and a switching device is a component of at least a propulsor motor.

A high voltage electric machine and power distribution system including one or more of such electric machines are provided. In one aspect, a high voltage electric machine includes a stator, a rotor, and a housing encasing at least a portion of the stator and rotor. The stator is modularized into cascaded voltage stator modules. The stator modules are galvanically isolated from one another by intermodular separators. At least one intermodular separator is positioned between each adjacent pair of stator modules. The stator modules are also galvanically isolated from the housing by a housing separator. The housing separator is positioned between the stator modules and the housing. Each stator module has an associated set of windings that are wound only within their associated stator module.

A power distribution system 100 is installed in an aircraft, and comprises: a first DC power supply unit 10 including a generator 11; a second DC power source unit 20 including a battery 30, a step-up/down converter 41, a voltage sensor 43, and control unit 44; and a diode 50. When the voltage sensor 43 does not detect regenerative power, the control unit 44 executes a running power processing mode in which generated power generated by the first DC power supply unit 10 is supplied to an electric actuator 80 while charging and discharging the battery 30 using the step-up/down converter 41 so as to keep a charge rate A of the battery 30 within a predetermined range. When the voltage sensor 43 detects regenerative power, the control unit 44 executes a regenerative power processing mode in which the battery 30 is charged with the regenerative power using the step-up/down converter 41.