An electronic system for a battery designed to supply electrical power to an application, such as in an aircraft, that includes a main power supply, comprises a charging circuit (30) with a charger (K3C), a first battery discharging circuit (20) in parallel with the charging circuit, a component ensuring continuity of discharge (D3) and an electronic control unit adapted to control opening and closing of the discharge switch (K2) and adapted to control said charger (K3C). The control unit keeps the battery charged as long as it is not being called on to discharge and interrupts battery charging and sets the discharge switch (K2) to the closed position when a call for power is detected from the application, the component ensuring continuity of discharge (D3) allowing passage of a discharge current during a transitional phase of closing of the discharge switch (K2).