A resonant transformer connected between a ground terminal and elevated terminal draws current from the earth's electric field through a primary winding of the transformer. An impulse generator applies a high voltage impulse to the primary winding of the resonant transformer to cause current to flow from the ground terminal through the primary winding. The flow of current through the primary winding of the resonant transformer induces a current in the secondary winding, which may be converted and filtered to a usable form, e.g. 60 Hz AC or DC.

A resonant transformer connected between a ground terminal and elevated terminal draws current from the earth's electric field through a primary winding of the transformer. An impulse generator applies a high voltage impulse to the primary winding of the resonant transformer to cause current to flow from the ground terminal through the primary winding. The flow of current through the primary winding of the resonant transformer induces a current in the secondary winding, which may be converted and filtered to a usable form, e.g. 60 Hz AC or DC.

Aircraft electric power distribution systems and methods of operating aircraft electrical power distribution systems are provided. One such method comprises determining a measure of an electrical power demand of a power and propulsion system of the aircraft; setting a target operating voltage of the aircraft electrical power distribution system based at least in part on the measure of the electrical power demand; and controlling the operating voltage in accordance with the set target operating voltage. In some embodiments the measure of the electrical power is a measure of an operating parameter of a gas turbine engine or propulsor of the aircraft.

Methods and systems for power management are disclosed. The disclosed power management may facilitate the use of different components that may have different electrical current capacity limitations. The current capacity limitations may be based on, for example, physical limitations of the components, regulatory limitations, organizational limitations, and/or other considerations. It may not be desirable to exceed the current capacity limitations. By implementing the disclosed power management methods, systems, and/or devices, operation of devices may be less likely to result in the current drawn through devices such as power cables exceeding the current capacity limitations even while other devices operably connected to the cables do not have such current capacity limitations.

Methods and systems for power management are disclosed. The disclosed power management may facilitate the use of different components that may have different electrical current capacity limitations. The current capacity limitations may be based on, for example, physical limitations of the components, regulatory limitations, organizational limitations, and/or other considerations. It may not be desirable to exceed the current capacity limitations. By implementing the disclosed power management methods, systems, and/or devices, operation of devices may be less likely to result in the current drawn through devices such as power cables exceeding the current capacity limitations even while other devices operably connected to the cables do not have such current capacity limitations.

In accordance with at least one aspect of this disclosure, a method for power distribution and load management in an aircraft can include budgeting a designated current for one or more loads in one or more respective power districts in a power distribution system based on a nominal load draw for each of the one or more loads, determining a system condition of the power distribution system, prioritizing each of the one or more loads based on the system condition, and distributing power from each of the one or more power districts to the respective one or more loads in order of priority until a total budgeted designated current for the respective power district has been exhausted, and leaving any remaining loads in the one or more power districts unpowered.

A system includes a transformer rectifier unit (TRU) including a backfeed sense module. A contactor is operatively connected to the TRU for selectively supplying DC power to a DC bus from the TRU with the contactor closed and isolating the DC bus from the TRU with the contactor opened. A contactor driver is operatively connected to receive a signal from the backfeed sense module and to control opening and closing of the contactor based on the signal. The contactor driver is configured to open the contactor upon receipt of the signal indicative of backfeed detected in the TRU.

A system includes a transformer rectifier unit (TRU) including a backfeed sense module. A contactor is operatively connected to the TRU for selectively supplying DC power to a DC bus from the TRU with the contactor closed and isolating the DC bus from the TRU with the contactor opened. A contactor driver is operatively connected to receive a signal from the backfeed sense module and to control opening and closing of the contactor based on the signal. The contactor driver is configured to open the contactor upon receipt of the signal indicative of backfeed detected in the TRU.

Electrical power systems for distributing electrical power in aircraft are described. One such electrical power system comprises: an electrical power source configured to output a number R≥2 of dc power channels, each dc power channel having a respective index r=(1, . . . , R); and a group of N dc load channels connected to the R dc power channels by a switching arrangement, wherein each dc load channel has a respective index n=(1, . . . , N) and R<N≤2R. The switching arrangement is operable to connect the r-th power channel to the n-th load channel according to a relationship r(n).

Electrical power systems for distributing electrical power in aircraft are described. One such electrical power system comprises: an electrical power source configured to output a number R≥2 of dc power channels, each dc power channel having a respective index r=(1, . . . , R); and a group of N dc load channels connected to the R dc power channels by a switching arrangement, wherein each dc load channel has a respective index n=(1, . . . , N) and R<N≤2R. The switching arrangement is operable to connect the r-th power channel to the n-th load channel according to a relationship r(n).