Abstract: The invention relates to a power supply system for several user systems onboard an aircraft. This system comprises at least two power supply electronics (10, 11) and means of connecting these at least two power supply electronics to at least two user systems (12, 13, 14, 15), characterised in that these connecting means comprise a network of connecting contactors (16, 17; 32, 33) from each power supply electronics with at least two user systems not performing similar functions but technologically compatible such that these power supply electronics supply these user systems at different times.

Abstract: A power system including at least two self-controlled synchronous machines operating in parallel synchronously, a central three-phase converter to which all these machines are connected in parallel, at least two rotor position sensors. The system also includes at least one control module that receives phase currents from each synchronous machine, signals output from position sensors, and a required reference torque value and that powers the three-phase central converter so as to slave the phase currents for each machine as a function of the required reference torque.

Abstract: The invention relates to a power system comprising at least two self-controlled synchronous machines (MS1, MS2) operating in parallel synchronously, a central three-phase converter (20; 50) to which all these machines are connected in parallel, at least two rotor position sensors (23, 24; 45, 46, 47, 48), characterised in that it comprises at least one control module (25; 30, 31; 53, 54, 55, 56) that receives phase currents from each synchronous machine, signals output from position sensors (23, 24), and a required reference torque value (Cref) and that powers the three-phase central converter (20) so as to slave the phase currents for each machine as a function of the required reference torque (Cref). The invention also concerns a control method for such a system.

Abstract: The invention relates to a power supply system for several user systems onboard an aircraft. This system comprises at least two power supply electronics (10, 11) and means of connecting these at least two power supply electronics to at least two user systems (12, 13, 14, 15), characterised in that these connecting means comprise a network of connecting contactors (16, 17; 32, 33) from each power supply electronics with at least two user systems not performing similar functions but technologically compatible such that these power supply electronics supply these user systems at different times.

Abstract: A multilevel converter including, in particular, a voltage source, a current source, and a capacitor for each of its cells, and a controller. The controller evaluates any current difference between an observed current through the current source and a current requested by the current source. The controller also includes ON-time controller for taking into account the current difference, if any, and altering accordingly a duration of the first conduction state of all of the cells in the converter in a direction suitable for reducing the current difference. The controller also maintains all of the floating capacitors at their equilibrium voltage values.