Power distribution architecture for actuating moving elements of an aircraft in sequence

1. An electrical power distribution architecture specially adapted for actuating in sequence aircraft moving elements such as doors, undercarriages, or high-lift elements, said moving elements being actuated by electromechanical actuators powered in sequence from electrical power delivered by at least one electrical power bus of the aircraft,

the architecture comprising at least one power distribution member comprising:

calibrator means for calibrating the electrical power coming from the power supply bus of the aircraft; and

switch means for selectively directing the calibrated electrical power to one or the other of the electromechanical actuators.

2. An architecture according to claim 1 , in which the calibrator means comprise an inverter associated with means for controlling it.

3. An architecture according to claim 1 , comprising at least two power distribution members, at least one of the moving elements being actuated by two electromechanical actuators each connected to one of the power distribution members.

4. An architecture according to claim 3 , in which the two power distribution members are powered by distinct power supply buses.

5. An architecture according to claim 1 , comprising at least two power distribution members, at least one of the moving elements being actuated by a single electromechanical actuator arranged to operate either with one or the other of the power distribution members, or else with both simultaneously.

6. An architecture according to claim 5 , in which the two power distribution members are powered by distinct power supply buses.

7. An architecture according to claim 5 , in which the two power distribution members are grouped together close to the electromechanical actuator(s) connected to said two distribution members.

8. An architecture according to claim 1 , comprising three groups of two power distribution members each, such that:

one of the groups is disposed close to a main undercarriage for powering the electromechanical actuators associated with said main undercarriage, and possibly other actuators;

one of the groups is disposed close to another main undercarriage to power the electromechanical actuators associated with said other main undercarriage, and possibly other actuators; and

one of the groups is disposed close to a nose undercarriage for powering the electromechanical actuators associated with said nose undercarriage, and possibly other actuators.

9. An architecture according to claim 8 , in which the power distribution members of at least one of the groups disposed close to a main undercarriage are arranged to power one or more electromechanical actuators of a high-lift system fitted to the aircraft.

10. An architecture according to claim 9 , in which the high-lift system includes at least two electromechanical actuators, one of the electromechanical actuators being associated with one of the power distribution members of one of the groups disposed close to one of the main undercarriages, while the other electromechanical actuator is associated with one of the power distribution members of the other of the groups disposed close to the other main undercarriage, the two power distribution members concerned being powered by distinct power supply buses.

11. An architecture according to claim 8 , in which the group of power distribution members disposed close to the nose undercarriage is also arranged to power a cargo door electromechanical actuator.

12. An architecture according to claim 1 , including a plurality of identical power distribution members.