An aircraft power distribution system comprising: a plurality of generators that generate respective AC voltage signals in response to mechanical energy generated by one or more aircraft turbines of an aircraft; a plurality of inverter-converter-controllers (54, 56, 58), each of the plurality of inverter-converter-controllers (54, 56, 58) including an AC/DC converters that receives a respective AC output signal from a respective generator and generate a respective DC voltage to provide a given amount of power; a plurality of dedicated DC buses, wherein each dedicated DC bus is associated with a respective generator and a respective AC/DC converter and to receive a respective DC voltage, each dedicated bus providing the given amount of power to one or more associated dedicated bus loads; a synchronization bus selectively coupleable to each dedicated DC bus by respective synchronization bus line switches to allow for bus sharing between a first set of dedicated DC buses of the plurality of dedicated DC buses and isolating a second set of selected dedicated DC buses of the plurality of dedicated DC buses a bus; a controller that controls selective closing and opening of the respective synchronization bus line switches and controls the given amount of power that the respective AC/DC converter provides when the respective synchronization bus line switch is in one of a closed state and open state based on a value determined based on aircraft operating parameters of the aircraft; and characterized in that the aircraft power system further comprises a vehicle management system to issue a load share command, to the plurality of inverter-converter-controllers (54, 56, 58), that governs a percentage of power that is supplied by each of the plurality of inverter-converter-controllers (54, 56, 58), wherein load share default ratios are programmed into each of the plurality of inverter-converter-controllers (54, 56, 58) based on maximum continuous output ratings of each generating system comprised of one of the plurality of generators, one of the plurality of inverter-converter-controllers (54, 56, 58), and one of the plurality of dedicated DC buses, and wherein the vehicle management system issues a command to revert the plurality of inverter-converter-controllers (54, 56, 58) to load share default ratios to reconfigure the aircraft power distribution system. a plurality of generators that generate respective AC voltage signals in response to mechanical energy generated by one or more aircraft turbines of an aircraft; a plurality of inverter-converter-controllers (54, 56, 58), each of the plurality of inverter-converter-controllers (54, 56, 58) including an AC/DC converters that receives a respective AC output signal from a respective generator and generate a respective DC voltage to provide a given amount of power; a plurality of dedicated DC buses, wherein each dedicated DC bus is associated with a respective generator and a respective AC/DC converter and to receive a respective DC voltage, each dedicated bus providing the given amount of power to one or more associated dedicated bus loads; a synchronization bus selectively coupleable to each dedicated DC bus by respective synchronization bus line switches to allow for bus sharing between a first set of dedicated DC buses of the plurality of dedicated DC buses and isolating a second set of selected dedicated DC buses of the plurality of dedicated DC buses a bus; a controller that controls selective closing and opening of the respective synchronization bus line switches and controls the given amount of power that the respective AC/DC converter provides when the respective synchronization bus line switch is in one of a closed state and open state based on a value determined based on aircraft operating parameters of the aircraft; and characterized in that the aircraft power system further comprises a vehicle management system to issue a load share command, to the plurality of inverter-converter-controllers (54, 56, 58), that governs a percentage of power that is supplied by each of the plurality of inverter-converter-controllers (54, 56, 58), wherein load share default ratios are programmed into each of the plurality of inverter-converter-controllers (54, 56, 58) based on maximum continuous output ratings of each generating system comprised of one of the plurality of generators, one of the plurality of inverter-converter-controllers (54, 56, 58), and one of the plurality of dedicated DC buses, and wherein the vehicle management system issues a command to revert the plurality of inverter-converter-controllers (54, 56, 58) to load share default ratios to reconfigure the aircraft power distribution system.