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: A system configured to deliver as output a polyphase current of constant frequency from a synchronous generator driven at variable speed. The system includes, at the output of the generator, an AC-to-DC active rectifier including one arm per phase of the current, a DC bus and a DC-to-AC inverter for the output including one arm per phase of the current, the inverter or the DC bus including an arm connected to the neutral, each arm including a controllable switch, the system including an electronic control unit driving the rectifier and including means for tracking a voltage for the rectifier and/or the inverter and means for controlling the inverter, the system including an EMC filter including one arm for each phase of the current, each arm including an inductor, a capacitor connected in a bypass downstream of the inductor, the arm connected to the neutral being connected to each bypass.

Abstract: The invention relates to an electric propulsion unit for an aircraft comprising at least one first propulsion member, a second propulsion member and a single electric motor configured to drive the first propulsion member and the second propulsion member in a counter-rotating manner, the electric motor comprising a peripheral stator element comprising a first peripheral stage and a second peripheral stage which are offset along an axis, the first peripheral stage comprising at least a first phase, a second phase and a third phase which are alternated according to a first sequence in such a way as to allow a rotation of the first rotor element in the first direction of rotation, the second peripheral stage comprising phases which are alternated according to a second sequence in such a way as to allow a counter-rotating rotation of the second rotor element.

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: The invention relates to an electric propulsion unit for an aircraft comprising at least one first propulsion member, a second propulsion member and a single electric motor configured to drive the first propulsion member and the second propulsion member in a counter-rotating manner, the electric motor comprising a peripheral stator element comprising a first peripheral stage and a second peripheral stage which are offset along an axis, the first peripheral stage comprising at least a first phase, a second phase and a third phase which are alternated according to a first sequence in such a way as to allow a rotation of the first rotor element in the first direction of rotation, the second peripheral stage comprising phases which are alternated according to a second sequence in such a way as to allow a counter-rotating rotation of the second rotor element.

Abstract: A system configured to deliver as output a polyphase current of constant frequency from a synchronous generator driven at variable speed. The system includes, at the output of the generator, an AC-to-DC active rectifier including one arm per phase of the current, a DC bus and a DC-to-AC inverter for the output including one arm per phase of the current, the inverter or the DC bus including an arm connected to the neutral, each arm including a controllable switch, the system including an electronic control unit driving the rectifier and including means for tracking a voltage for the rectifier and/or the inverter and means for controlling the inverter, the system including an EMC filter including one arm for each phase of the current, each arm including an inductor, a capacitor connected in a bypass downstream of the inductor, the arm connected to the neutral being connected to each bypass.