Abstract: The present invention relates to a system for converting and transporting electrical energy in a turbomachine-propelled aircraft, said system including: at least a first rotary electric machine connected mechanically to the low-pressure shaft by means of a coupling device, a second rotary electric machine connected mechanically to the high-pressure shaft by means of an accessory gearbox, and said first electric power module and said second electric power module being connected electrically to an internal electrical network of the turbomachine, a generator coupled to the accessory gearbox and intended to supply an electrical network of the aircraft with electricity, and a control device for controlling start-up of the turbomachine by at least one rotary electric machine, for compensating for power consumed by the generator, and for implementing distribution between the power absorbed by the high-pressure shaft and the power absorbed by the low-pressure shaft.

Abstract: An electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft which includes a high-voltage DC propulsive electric distribution network, a non-propulsive electric distribution network which is connected to loads of the aircraft, and an electric distribution network which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

Abstract: An aircraft with hybrid thermal/electrical propulsion includes a turbomachine; a first electrical source; a second electrical source equipped with an electrical energy storage device; a non-propulsion electrical distribution network; a low-voltage electrical distribution network; and a propulsion electrical distribution network. The three electrical distribution networks are electrically supplied by the first and second electrical sources and electrically interconnected by static converters.

Abstract: A system for controlling an aircraft power network including at least a first propulsion assembly having at least one left-hand starter-generator and a second propulsion assembly having at least one right-hand starter-generator as well as other electrical motors, the system including first and second power electronics boxes each including at least two so-called generic control boards for controlling the power network, each of these at least two generic control electronics boards being connected by a fast communication link to separate first and second data switches, the first and second data switches of the first power electronics box being respectively connected to the first and second data switches of the second power electronics box by a first fast communication bus.

Abstract: An electrical module configured to be connected to a power shaft of a turbine engine of an aircraft. The electrical module being configured to draw off power from/inject power into the power shaft. The electrical module comprising an electric machine comprising a machine housing in which a stator and a rotor is mounted, configured to be mechanically connected to the power shaft, the machine housing having a cylindrical shape extending along a cylinder axis, a first electric converter mounted in a first housing, a second electric converter mounted in a second housing, the second converter being independent of the first converter, the first housing and the second housing each being in the shape of a half-cylinder extending along the cylinder axis so as to form a cylindrical assembly that is mounted as an extension of the machine housing of the electric machine to limit the size of the electrical module.

Abstract: Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises: —an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm2, and— an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.

Abstract: Disclosed is an electrically conductive rigid bar (80) for electrically connecting an electric machine (70) of an aircraft turbine engine, characterised in that it comprises:- an elongate body (80a) made from electrically conductive material having a polygonal cross-section greater than or equal to 50 mm2, and - an electrical insulation sheath (80b) that surrounds the body, at least one of the longitudinal ends (84a) of the body not being covered by the sheath and comprising a through-hole (86) in which a bolt (88) for fastening and electrically connecting this end is mounted.

Abstract: The invention relates to an electric architecture for a twin-engined, hybrid thermal/electric propulsion aircraft and, for each turboshaft engine, the architecture comprises: —a high-voltage DC propulsive electric distribution network (32), —a non-propulsive electric distribution network (56) which is connected to loads of the aircraft, and—an electric distribution network (76) which is connected to loads of an electrified control system of the turboshaft engine, and wherein power supply sources are shared for these different networks.

Abstract: A system for controlling an aircraft power network including at least a first propulsion assembly having at least one left-hand starter-generator and a second propulsion assembly having at least one right-hand starter-generator as well as other electrical motors, the system including first and second power electronics boxes each including at least two so-called generic control boards for controlling the power network, each of these at least two generic control electronics boards being connected by a fast communication link to separate first and second data switches, the first and second data switches of the first power electronics box being respectively connected to the first and second data switches of the second power electronics box by a first fast communication bus.

Abstract: An aircraft with hybrid thermal/electrical propulsion includes a turbomachine; a first electrical source; a second electrical source equipped with an electrical energy storage device; a non-propulsion electrical distribution network; a low-voltage electrical distribution network; and a propulsion electrical distribution network. The three electrical distribution networks are electrically supplied by the first and second electrical sources and electrically interconnected by static converters.