A power distribution circuit for an electrically powered aircraft includes a plurality of batteries and a plurality of electric propulsion systems. A plurality of isolated power distribution circuits each couple a battery of the plurality of batteries to two or more electric propulsion systems. The plurality of electric propulsion systems are positioned on the aircraft to apply balanced forces to the aircraft such that in the event of a failure, the aircraft remains stable and only experiences a loss in altitude or speed.

A power distribution system includes a first electrical bus coupled to a first power source for providing electrical power to the first electrical bus; a second electrical bus coupled to a second power source for providing electrical power to the second electrical bus; a bus bridge for selectively coupling the first and second electrical buses, and including a first power control device including a first switch coupled between the first electrical bus and the second electrical bus, and configured to perform determining whether a second fault signal indicating failure of the second power source has been received; determining whether a reverse current is flowing from the second electrical bus to the first electrical bus; and in response to determining that the reverse current is flowing and determining that the second fault signal is not received, activating the first switch to enable current flow between the first and second electrical buses.

A wireless power system, preferably including a set of one or more substrates and a wireless power receiver, wherein the wireless power receiver preferably includes one or more radio frequency (RF) impedance sheets. A method of operation for a wireless power system, preferably including receiving power wirelessly and/or delivering power to one or more electrical loads, and optionally include deploying the system and/or stowing the system S240.

An electrical machine with a rotor coupled to a drive shaft of an engine; a DC electrical network; a power electronics converter connected, on a DC-side, to the DC electrical network, and, on an AC-side, to the electrical machine, the power electronics converter comprising a plurality of transistors and associated diodes connected in anti-parallel with the transistors; and a controller configured to control switching of the transistors so that the converter either inverts DC power to AC power or rectifies AC power to DC power. The controller is further configured, responsive to a determination that there is a fault in the DC electrical network, to operate in a fault mode in which the controller controls the switching of the transistors so that a fault current is shared between the transistors and the associated diodes.

A power source assembly includes a plurality of strings electrically connectable to a load. Each of the plurality of strings includes a fuel cell module and a DC/DC converter electrically connected to the fuel cell module. Each of the plurality of strings is arranged in parallel to each other of the plurality of strings.

A smart battery includes a battery and a measurement module coupled to measure electrical characteristics of the battery. The smart battery also includes processing logic and a communication interface configured to receive the electrical characteristics and transmit the electrical characteristics to a receiver.

A method for detecting a failure in a line portion of a DC electrical power supply network, the line portion includes, for a given current direction, a single electrical conductor wire or a plurality of electrical conductor wires electrically connected together in series via at least one terminal block, the method includes: at a first end of the line portion, injecting a signal; at a second end of the line portion, receiving said signal; and deciding that there is a failure in the line portion, if at least one predetermined difference criterion, between the injected signal and the received signal, is satisfied. Thus, serial electrical discontinuities along the line can easily be detected.

An electric assembly for an aircraft is provided that includes a battery string, a switch, a battery charging system, and a charge monitoring device. The battery string includes a plurality of battery modules and a contactor. The plurality of battery modules are electrically connected in series. The contactor is disposable in an open configuration or a closed configuration. The battery charging system is in communication with the battery string, and configured to perform a charging operation of the battery string. The charge monitoring device includes a processor and non-transitory memory. The non-transitory memory stores instructions executable by the processor, causing the processor to determine a charging parameter of the contactor, identify the presence of a fault condition for the contactor, and signal the switch to actuate the contactor to the open configuration. The presence of the fault condition indicates the charging parameter exceeds the fault condition threshold.

A wireless power system, preferably including a set of one or more substrates and a wireless power receiver, wherein the wireless power receiver preferably includes one or more radio frequency (RF) impedance sheets. A method of operation for a wireless power system, preferably including receiving power wirelessly and/or delivering power to one or more electrical loads, and optionally include deploying the system and/or stowing the system S240.

A power supply system for use in an airplane is described. The power supply system includes N alternating current (AC) power outlets configured to provide AC power output at a passenger seat in an airplane, M direct current (DC) power outlets configured to provide DC power output at the passenger seat and a controller configured to control allocation of power from a power supply to the N AC power outlets and M DC power outlet according to a phase of a plurality of phases of operation of the power supply system, where N and M are positive integers.