Abstract: A system for controlling idle speed and power draw includes a determination unit configured to determine a current available power value, a determination unit configured to determine a current power consumption value, a determination unit configured to determine a future power requirement variation value, a computation unit configured to calculate a future estimated total power requirement value, a computation unit configured to calculate a future estimated available power value, an optimization unit configured to determine an optimization result by comparing the estimated total power requirement value with a power value associated with an optimization criterion and a controller configured to send an order to adapt an idle speed of the engine, an order to adapt the estimated total power requirement or no order as a function of the optimization result.

Abstract: A method for managing power drawn from power units of propulsion units of an aircraft, wherein the method includes a step of increasing the amount of power drawn from a second power unit that is time shifted, with respect to a step of increasing the amount of power drawn from a first power unit, for a duration that at least allows the operational state or the non-operational state of the first power unit to be determined. This solution allows simultaneous switching to the non-operational state of the two power units to be avoided.

Abstract: A method for managing the offtake of power produced by an auxiliary power unit of an aircraft. The method comprises a step of calculating a maximum capacity for offtake of mechanical power that the auxiliary power unit can provide to the aircraft, a step of determining an actual offtake of mechanical power taken off by a first mechanical power offtake system of the auxiliary power unit, a step of comparing the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, a step of optimizing the offtake of mechanical power which step, based on the comparison of the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, determines at least one corrective action. A device for managing the offtake of power produced by an auxiliary power unit of an aircraft and an aircraft including such a device are provided.

Abstract: A system for controlling idle speed and power draw includes a determination unit configured to determine a current available power value, a determination unit configured to determine a current power consumption value, a determination unit configured to determine a future power requirement variation value, a computation unit configured to calculate a future estimated total power requirement value, a computation unit configured to calculate a future estimated available power value, an optimization unit configured to determine an optimization result by comparing the estimated total power requirement value with a power value associated with an optimization criterion and a controller configured to send an order to adapt an idle speed of the engine, an order to adapt the estimated total power requirement or no order as a function of the optimization result.

Abstract: A method for managing the offtake of power produced by an auxiliary power unit of an aircraft. The method comprises a step of calculating a maximum capacity for offtake of mechanical power that the auxiliary power unit can provide to the aircraft, a step of determining an actual offtake of mechanical power taken off by a first mechanical power offtake system of the auxiliary power unit, a step of comparing the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, a step of optimizing the offtake of mechanical power which step, based on the comparison of the maximum capacity for offtake of mechanical power and the actual offtake of mechanical power, determines at least one corrective action. A device for managing the offtake of power produced by an auxiliary power unit of an aircraft and an aircraft including such a device are provided.

Abstract: A method for controlling takeoffs of mechanical energy and/or air on a turbine engine for the propulsion of an aircraft. It is based on a protocol for the exchange of a request/authorization between and by the energy manager and a system for controlling the turbine engine. This protocol is implemented as a result of a modification of the takeoff requirement. It is intended to check whether the surge margin is compatible with the modification of the takeoff requirement and, if the need arises, to apply temporary measures in order to prevent surge in the turbine engine, for example by providing at least a part of the energy requirements by a buffer. This permits the optimization of the operation of a turbine engine for the propulsion of an aircraft, while avoiding the risk of surge of the turbine engine.

Abstract: A system and a method for the automatic starting of the engines of a twin-engine aircraft. When a first engine is made by the pilots of the aircraft to follow an automatic starting procedure, this engine follows the conventional four-phase starting cycle. The rotor of the high-pressure stage of the second engine is spun up for a predetermined duration and to a speed that is substantially constant and less than the nominal value during the starting cycle for the first engine. Once the starting cycle for the first engine is complete, the second engine is made by the pilots of the aircraft to follow an automatic starting procedure. The starting cycle for the second engine comprises just three phases.

Abstract: A method for controlling takeoffs of mechanical energy and/or air on a turbine engine for the propulsion of an aircraft. It is based on a protocol for the exchange of a request/authorization between and by the energy manager and a system for controlling the turbine engine. This protocol is implemented as a result of a modification of the takeoff requirement. It is intended to check whether the surge margin is compatible with the modification of the takeoff requirement and, if the need arises, to apply temporary measures in order to prevent surge in the turbine engine, for example by providing at least a part of the energy requirements by a buffer. This permits the optimization of the operation of a turbine engine for the propulsion of an aircraft, while avoiding the risk of surge of the turbine engine.

Abstract: The subject of the disclosure is an aircraft comprising at least one left motor generator, at least one right motor generator, a control device for a jet pipe nozzle with variable cross-section of the aircraft comprising at least one control member powered by a first airplane electrical power supply linked to at least one right or left motor generator, the control member powered by a second electrical power supply linked to an electrical power source of the aircraft independent of the first airplane electrical power supply.

Abstract: A system and a method for the automatic starting of the engines of a twin-engine aircraft. When a first engine is made by the pilots of the aircraft to follow an automatic starting procedure, this engine follows the conventional four-phase starting cycle. The rotor of the high-pressure stage of the second engine is spun up for a predetermined duration and to a speed that is substantially constant and less than the nominal value during the starting cycle for the first engine. Once the starting cycle for the first engine is complete, the second engine is made by the pilots of the aircraft to follow an automatic starting procedure. The starting cycle for the second engine comprises just three phases.

Abstract: The subject of the disclosure is an aircraft comprising at least one left motor generator, at least one right motor generator, a control device for a jet pipe nozzle with variable cross-section of the aircraft comprising at least one control member powered by a first airplane electrical power supply linked to at least one right or left motor generator, the control member powered by a second electrical power supply linked to an electrical power source of the aircraft independent of the first airplane electrical power supply.