WO WO2026109862A1
The invention relates to an aircraft series-hybrid electric propulsion assembly, the propulsion assembly comprising: - an electric turbogenerator (110) comprising at least one turbine engine (112) and at least one generator (114) coupled to the turbine engine; - a storage battery (125); - an HVDC bus (130) coupled to the turbogenerator and to the battery (125), the turbogenerator (110) being connected to the HVDC bus (130) via an alternating-current (AC) to direct-current (DC) rectifier (116) connected to phases of the at least one generator (114), the battery (125) being connected directly to the high-voltage direct-current (HVDC) electrical network, the turbogenerator (110) and the battery (125) sharing the power required to supply the HVDC bus (130); - a control system (115) for controlling the rectifier (116), the control system being configured to control the rectifier (116) and to manage electrical power sharing provided on the HVDC bus (130) between the turbogenerator (110) and the battery (125) on the basis of the setpoint control of at least the current (IBAT) delivered by the battery (125), by modulating the output voltage (UBUS) of the rectifier (116) via at least one control signal (CMD), in particular by pulse-width modulation.
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