Abstract: Provided is an induction heating method implemented in a device for heating a metal part, the device including magnetically coupled inductors. Oscillating circuits of the device have at least approximately the same resonance frequency, each inverter is controlled by a control unit to vary amplitude and phase of current passing through the corresponding inductor, the device also including a means for determining said current and an actual temperature profile of said part. The method includes: a) comparing said actual temperature profile with a reference temperature profile and calculating a reference power density profile; b) calculating target currents which the inverters must produce in order for the currents of the inductors to reach suitable target values; c) determining the currents passing through the inductors to compare said currents with said target values and determine correction current deviations, and sending correction instructions to said control units in accordance with said current deviations.

Abstract: Provided is an induction heating method implemented in a device for heating a metal part, the device including magnetically coupled inductors. Oscillating circuits of the device have at least approximately the same resonance frequency, each inverter is controlled by a control unit to vary amplitude and phase of current passing through the corresponding inductor, the device also including a means for determining said current and an actual temperature profile of said part. The method includes: a) comparing said actual temperature profile with a reference temperature profile and calculating a reference power density profile; b) calculating target currents which the inverters must produce in order for the currents of the inductors to reach suitable target values; c) determining the currents passing through the inductors to compare said currents with said target values and determine correction current deviations, and sending correction instructions to said control units in accordance with said current deviations.

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.