Electrical power distribution systems manage the allocation of power from energy sources to electrical loads that consume distributed electrical power. In aircraft, gas turbine engines that propel the aircraft typically also provide mechanical energy that ultimately powers a number of different accessories such as generators, starter/generators, permanent magnet alternators (PMA), fuel pumps, and hydraulic pumps, i.e., equipment for aircraft functions other than propulsion. As well, contemporary aircraft need electrical power for electrical loads related to avionics, communications, motors, and other electric equipment.
Over time, aircraft electrical power source voltages have increased. Aircraft with 14- and 28-volt direct current (VDC) electrical power systems have given way to aircraft with electrical power systems operating at 115 volts alternative current (VAC) and 230 VAC. Presently, aircraft can include one or more electrical power sources that operate at voltages including plus/minus 270 VDC and deliver high current that often ranges, for example, from 40 to 100 Amperes. A current wide-body twin-engine commercial jet liner uses a hybrid voltage electrical system that includes sub-systems operating at voltages of 230 VAC, 115 VAC, 28 VDC along with a bipolar, high voltage, direct current subsystem that includes plus and minus 270 VDC sources.
Electrical power distribution systems typically include one or more solid-state power controllers (SSPC). In order to meet the requirements of ever higher current ratings in SSPCs, arrays of solid-state devices are interconnected to lower the total impedance of the SSPC. As these arrays include more elements to meet overall impedance requirements of the SSPC, the design of the controller becomes complicated. That is, an SSPC that includes a large number of solid-state switching elements can have a complex interconnect and mounting scheme.