Patent ID: 9487166
Filing Date: 2016-11-08
CPC Classification: B60R,B64D,H02J

Claim Text:
1. An aircraft electrical system, comprising: an electrical network, designed to electrically power at least one functional equipment of the aircraft; a regulating assembly capable of maintaining a desired electrical power on the electrical network, the desired electrical power being provided by at least one electricity generating assembly of the aircraft, the electricity generating assembly being coupled to at least an engine of the aircraft; wherein the regulating assembly includes: a secondary electrical power source; a conversion assembly for additional electrical power injected on the electrical network, the conversion assembly is configured, in a first electrical regulating configuration, to consume the additional electrical power present on the electrical network to create at least one supply fluid for a secondary source; a reservoir for each supply fluid, inserted between the conversion assembly and the secondary source to collect the supply fluid produced by the conversion assembly, wherein the secondary source is formed by a fuel cell, wherein the conversion assembly includes an electrolyzer, and wherein the regulating assembly can be driven between: a standby configuration, in which the secondary source is supplied by a first supply fluid flow rate coming from each reservoir to produce a first standby electrical power, the first electrical regulating configuration, and a second electrical regulating configuration, and in the second regulating configuration, the secondary source is supplied by a second supply fluid flow rate coming from each reservoir, the second flow rate being higher than the first flow rate to produce a second electrical regulating power higher than the first standby electric power.