Patent ID: 7482709
Filing Date: 2009-01-27
Classification: H02J

Abstract:
1. A system for powering and controlling electrical equipment of an aircraft engine or of an environment of said aircraft engine, the system comprising: at least one DC voltage power supply bus; at least one set of power supply modules connected in parallel to the power supply bus, said set being associated with a respective group of pieces of electrical equipment for said aircraft engine or for said environment of said aircraft engine, the number of modules of the set being greater than the minimum number needed to activate the electrical equipment of the group so as to provide at least one emergency module, each module comprising a voltage converter for supplying an alternating voltage at the output from the module and derived from the DC voltage of the power supply bus; a selector circuit inserted between the outputs of the modules of the set of modules and the pieces of equipment of the equipment group; and a control device for controlling the modules and the selector circuit to activate each piece of equipment of the equipment group by connecting it to at least one of the modules, and to put an emergency module into service in the event of a failure being detected in one of the other modules, wherein the control device comprises a central control unit and processor units integrated respectively in the various modules to control the supply of alternative voltage by a module to a piece of electrical equipment powered by said module as a function of information transmitted by the central control unit, and wherein the or each emergency module is configurable to be adapted to any of the equipment to which it might be connected, by the central control unit changing an application program in the processor unit of the emergency module.