Abstract: An electrical network of an aircraft and a method of operation comprises: an AC bus, a DC bus, a rectifier providing a DC voltage to the DC bus with the help of the AC bus, a plurality of bidirectional converters comprising two linkup points, each bidirectional converter being linked up at its first linkup point to the DC bus and being able to be linked up at its second linkup point to a load of the aircraft so as to power it, the network being able to be linked up to at least two generators each capable of delivering the AC voltage to the AC bus by the rectifier. At least one link links up at least one of the generators to the second linkup point of at least one of the bidirectional converters. The network can change generator with no cutoff and with no particular synchronization of the generators.

Abstract: The invention relates to a method for managing an electrical network. The electrical network includes two power centers making it possible for each one to supply several loads, each power center including: an electrical power supply bus, a plurality of reversible converters making it possible to exchange energy between the bus and the various loads , routing means making it possible to vary an association between the converters and the loads, an energy storage element. According to the invention, if for a first of the power centers, the regenerated power cannot be dissipated in the other loads associated with the first center, the regenerative load dissipates its power toward the bus of the second power center.

Abstract: An electrical network of an aircraft and a method of operation comprises: an AC bus, a DC bus, a rectifier providing a DC voltage to the DC bus with the help of the AC bus, a plurality of bidirectional converters comprising two linkup points, each bidirectional converter being linked up at its first linkup point to the DC bus and being able to be linked up at its second linkup point to a load of the aircraft so as to power it, the network being able to be linked up to at least two generators each capable of delivering the AC voltage to the AC bus by the rectifier. At least one link links up at least one of the generators to the second linkup point of at least one of the bidirectional converters. The network can change generator with no cutoff and with no particular synchronization of the generators.

Abstract: The invention relates to a method for managing an electrical network. The electrical network includes two power centers making it possible for each one to supply several loads, each power center including: an electrical power supply bus, a plurality of reversible converters making it possible to exchange energy between the bus and the various loads , routing means making it possible to vary an association between the converters and the loads, an energy storage element. According to the invention, if for a first of the power centers, the regenerated power cannot be dissipated in the other loads associated with the first center, the regenerative load dissipates its power toward the bus of the second power center.

Abstract: The invention relates to an electrical network, which includes: two items of equipment able either to provide, or to consume electrical energy, transfer means hooked up between the two items of equipment and allowing the two items of equipment to exchange energy. The transfer means includes a reversible DC/AC converter, the converter being operated in voltage step-down or step-up DC/DC mode. In one embodiment of the invention, the first item of equipment is a high-voltage DC bus, and the network includes second items of equipment such as loads and a low-voltage DC bus to which a battery may be connected. The network includes several non-dedicated converters that can be connected between the first item of equipment and any of the second items of equipment.

Abstract: The invention relates to a device for powering a plurality of loads from an electrical power supply network. The invention is of particular use in the aeronautical domain. The device comprises a number of converters (EPPi) each comprising an input and an output, the input of each converter (EPPi) taking power from the network and the output of each converter (EPPi) being associated with at least one load (Li) to deliver power to it. The device comprises switching means (B1 to B6) enabling the association between converters (EPPi) and loads (Li) to be varied.

Abstract: A device for starting a gas turbine in an aircraft includes an electrical power supply delivering a direct current and a drive electric motor connected to the power supply, independent of the turbine to be started and having an output shaft mechanically coupled to an input shaft of the turbine to rotate with it. The drive electric motor is a three-phase alternating current synchronous motor and is controlled by an inverter connected to the power supply. Applications include situations in which the turbine to be driven is a high-power turbine.