Patent ID: 8662445

Claim:
A hybrid power distribution system for use in an aircraft having at least one engine, the hybrid power distribution system comprising: a starter drive/generator that converts mechanical energy provided by the at least one engine to electrical energy for distribution via an electrical power distribution bus; a pneumatic distribution channel for extracting low-pressure bleed air from the at least one engine; an environmental control system (ECS) connected to receive low-pressure bleed air from the pneumatic distribution channel, wherein the ECS includes temperature control components supplied with power from the electrical power distribution bus to provide cooling and heating to the low-pressure bleed air provided from the pneumatic distribution channel; a hydraulic distribution channel for providing hydraulic power to loads on the aircraft; an engine-driven pump connected to convert mechanical energy provided by the at least one engine to hydraulic energy in the hydraulic distribution channel; an electric-driven motor pump for converting electric energy provided by the electrical distribution bus to hydraulic energy for distribution by the hydraulic distribution circuit; and an air-driven pump for converting pneumatic energy provided by the pneumatic distribution circuit to hydraulic energy for distribution by the hydraulic distribution circuit, wherein hydraulic power is generated in the hydraulic distribution circuit by one of the engine-driven pump, the electric-driven motor pump, and air-driven pump during various flight segments based on which supplies the hydraulic power most efficiently.