Abstract: An aircraft comprises a fuselage, at least a first electrical generator and a second electrical generator, a set of electrical equipment items distributed in the fuselage and an electrical power distribution network comprising a switching system and a set of buses. The buses comprise at least a first bus and a second bus extending, at least partly, in a longitudinal direction of the fuselage and following segregated paths in the fuselage. In a normal mode of operation, the switching system links the first electrical generator to the first bus and the second electrical generator to the second bus. Each bus comprises connection points at different locations distributed along its length and each of the electrical equipment items is linked to a connection point of a bus via a local electrical power supply link.

Abstract: An aircraft comprises a fuselage, a set of electrical equipment items distributed in the fuselage, and a hybrid electrical power distribution and data communication network. The latter comprises a set of buses comprising at least one electrical power distribution bus extending, at least partly, in a longitudinal direction of the fuselage. A set of data links is associated with each bus of the set of buses. The bus and the associated set of data links each comprise connection points at different locations distributed along their length, forming pairs of connection points. Each of the electrical equipment items of the set of electrical equipment items is linked to a pair of connection points via a local electrical power supply link and/or via a local data link.

Abstract: A system for managing short-circuits in an aircraft meshed electrical energy distribution network, comprising nodes connected to one another by inter-node links forming a mesh of the network. A system node comprises a switch, a current limiter, circuitry elements to measure the current intensity circulating on the link and circuitry elements to measure a voltage drop on the link, and a control unit configured to acquire a link current measurement, compare the measurement with a predetermined current threshold and, if the measurement exceeds this threshold, command the current limiter to limit the link current, acquire a link voltage drop measurement, determine a time associated with the value of the voltage drop and check whether the voltage drop is still present after a time period equal to the time obtained, and if the voltage drop is still present then, command the opening of the switch corresponding to this link.

Abstract: An aircraft comprises a fuselage, at least a first electrical generator and a second electrical generator, a set of electrical equipment items distributed in the fuselage and an electrical power distribution network comprising a switching system and a set of buses. The buses comprise at least a first bus and a second bus extending, at least partly, in a longitudinal direction of the fuselage and following segregated paths in the fuselage. In a normal mode of operation, the switching system links the first electrical generator to the first bus and the second electrical generator to the second bus. Each bus comprises connection points at different locations distributed along its length and each of the electrical equipment items is linked to a connection point of a bus via a local electrical power supply link.

Abstract: An aircraft comprises a fuselage, a set of electrical equipment items distributed in the fuselage, and a hybrid electrical power distribution and data communication network. The latter comprises a set of buses comprising at least one electrical power distribution bus extending, at least partly, in a longitudinal direction of the fuselage. A set of data links is associated with each bus of the set of buses. The bus and the associated set of data links each comprise connection points at different locations distributed along their length, forming pairs of connection points. Each of the electrical equipment items of the set of electrical equipment items is linked to a pair of connection points via a local electrical power supply link and/or via a local data link.

Abstract: A system for managing short-circuits in an aircraft meshed electrical energy distribution network, comprising nodes connected to one another by inter-node links forming a mesh of the network. A system node comprises a switch, a current limiter, circuitry elements to measure the current intensity circulating on the link and circuitry elements to measure a voltage drop on the link, and a control unit configured to acquire a link current measurement, compare the measurement with a predetermined current threshold and, if the measurement exceeds this threshold, command the current limiter to limit the link current, acquire a link voltage drop measurement, determine a time associated with the value of the voltage drop and check whether the voltage drop is still present after a time period equal to the time obtained, and if the voltage drop is still present then, command the opening of the switch corresponding to this link.

Abstract: The present invention essentially relates to an electric machine (1.1) with homopolar double excitation, comprising a rotor particularly consisting of a central portion (51) made of a solid magnetic material and a laminated annular portion (53) located at the periphery of the solid portion. In addition, the rotor comprises permanent magnets (54), the magnetization thereof being radially oriented relative to the axis (33) of the rotor (31), and separated from one another such that the double excitation flow generated by the field coils (38, 39) can enter the rotor (31, 67) via the flanges (48, 49) of the rotor, and come back out via the spaces between the magnets (54), or vice-versa.

Abstract: The present invention essentially relates to an electric machine (1.1) with homopolar double excitation, comprising a rotor particularly consisting of a central portion (51) made of a solid magnetic material and a laminated annular portion (53) located at the periphery of the solid portion. In addition, the rotor comprises permanent magnets (54), the magnetisation thereof being radially oriented relative to the axis (33) of the rotor (31), and separated from one another such that the double excitation flow generated by the field coils (38, 39) can enter the rotor (31, 67) via the flanges (48, 49) of the rotor, and come back out via the spaces between the magnets (54), or vice-versa.