Patent ID: 7939962

Claim:
A power supply system for multiple aircraft systems of an aircraft, the power supply system comprising: a plurality of electric power supply units; a plurality of aircraft system units that include air conditioning, flaps, slats, thrust reversers, landing gear, engine start-up, doors, spoilers, and brakes; and a network of contactors configured to establish electrical connections between the plurality of aircraft system units and the plurality of electric power supply units, wherein the plurality of electric power supply units include, a first electric power supply unit configured to supply power to the air conditioning, a first flap, the thrust reverser, a first spoiler, a brake accumulator, and the engine start-up, but only one at a time, a second electric power supply unit configured to supply power to the air conditioning, a first slat, the landing gear, the doors, airbrakes, the brake accumulator, and the engine start-up, but only one at a time, a third electric power supply unit configured to supply power to the air conditioning, a second flap, the thrust reverser, a first spoiler, the brake accumulator, and the engine start-up, but only one at a time, and a fourth electric power supply unit configured to supply power to the air conditioning, the engine start-up, a second slat, the thrust reverser, the doors, the airbrakes, and the brake accumulators, but only one at a time, and the network of contactors is configured to cause the first, second, third, and fourth electric power supplies to supply power to subcombinations of the plurality of aircraft system units at different flight phases of the aircraft and to provide redundancy without a stand-by electric power supply unit, there being no unused electric power supply units during the flight phases of the aircraft, and no mutualization of two redundant systems.