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A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first

A flight control system for an aircraft, intended for controlling a plurality of actuators adapted for actuating control surfaces of the aircraft from information supplied by piloting members and/or sensors of the aircraft. The system includes a primary control system adapted for controlling a first set of control surface actuators and a secondary control system adapted for controlling a second set of control surface actuators, the primary and secondary systems being respectively powered by independent energy sources of different types.

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1. A flight control system for an aircraft to control a plurality of actuators adapted for actuating control surfaces of the aircraft based on information supplied by one or more of piloting members and sensors of the aircraft, comprising: a primary control system to control a first set of control s

1. A flight control system for an aircraft to control a plurality of actuators adapted for actuating control surfaces of the aircraft based on information supplied by one or more of piloting members and sensors of the aircraft, comprising: a primary control system to control a first set of control surface actuators of the aircraft, the primary control system including a first primary computer and a second primary computer, each said primary computer having the same structure, with generic computation modules, and being respectively powered by a first primary energy source and a second primary energy source; anda secondary control system to control a second set of control surface actuators of the aircraft, different from the first set of control surface actuators, the secondary control system including at least one secondary computer and a back-up computer, each said secondary computer having specific computation modules with an architecture specific to flight control computations and being powered by a secondary energy source,wherein the primary control system is independent from the secondary control system such that failure of the primary control system does not cause failure of the secondary control system and such that failure of the secondary control system does not cause failure of the primary control system,wherein the primary and secondary energy sources are independent from each other and are of different type of energy generating principle,wherein a first network is associated with the primary control system and a second network is associated with the secondary control system, the first network having a first protocol and the second network having a second protocol different from the first protocol, and the first network being independent from the second network,wherein the first and second primary energy sources are independent from each other,wherein each said secondary computer and the back-up computer of the secondary control system are powered by the secondary energy source and share the second set of actuators,wherein the primary control system is configured to control the first set of control surface actuators and not the second set of control surface actuators, andwherein the secondary control system is configured to control the second set of control surface actuators and not the first set of control surface actuators. 2. The flight control system according to claim 1, wherein each said primary computer is connected to the first network, which is a primary network, a first plurality of terminals subscribing to the primary network being adapted to acquire signals provided by a first set of sensors, a second plurality of terminals subscribing to the primary network being able to receive commands from the primary computer and to transmit electric orders to actuators belonging to the first set of actuators. 3. The flight control system according to claim 2, wherein a node of the primary network associated with the first primary computer and a node of the primary network associated with the second primary computer are connected by a link. 4. The flight control system according to claim 2, wherein at least one cluster of terminals subscribed to the primary network is connected to a micro-switch, the micro-switch being configured to receive, on a first port, frames sent by the primary computer intended for at least one terminal of the cluster and to receive, on a plurality of second ports, frames respectively sent by the different terminals of the cluster, the micro-switch having a repeater function for downlink operation and a multiplexer function for uplink operation. 5. The flight control system according to claim 2, wherein each said primary computer is connected to a concentrator via its associated primary network, the concentrator being configured to receive information provided by a plurality of the piloting members, to multiplex the information, and to send the information thus multiplexed to the primary computer. 6. The flight control system according to claim 1, wherein each said primary computer includes at least one pair of the generic computation modules, the at least one pair of generic computation modules including a control module and a monitoring module. 7. The flight control system according to claim 6, wherein each said primary computer includes first and second pairs of the generic computation modules, the second pair taking over control computations if the first pair fails. 8. The flight control system according to claim 6, wherein each said primary computer includes a triplet of independent generic computation modules, each said specific module performing same control computations in parallel from information provided by at least one of the piloting members and the sensors, control values obtained by the triplet of independent generic computation modules being compared to select values given by a majority. 9. The flight control system according to claim 1, wherein each said primary computer includes a pair of the generic computation modules, including a control module, a monitoring module, and a reserve module configured as an additional control module or an additional monitoring module in a case of failure of one or the other of the modules of the pair of generic computation modules. 10. The flight control system according to claim 1, wherein said at least one secondary computer includes a pair of the specific computation modules, the pair of specific computation modules including a control module and a monitoring module. 11. The flight control system according to claim 10, wherein the secondary control system further includes a specific reserve module configured as a reserve control module or a reserve monitoring module in event of a failure of any of the modules of the pair of specific computation modules. 12. The flight control system according to claim 10, wherein each said secondary computer includes a triplet of independent specific computation modules, each said specific computation module performing same control computations in parallel from information provided by piloting members, control values obtained by the triplet of independent specific computation modules being compared to select values given by a majority. 13. The flight control system according to claim 10, wherein the second network associated with the secondary control system is a secondary network, each said secondary computer being connected to the secondary network, a first plurality of terminals connected to the secondary network being configured to acquire signals provided by a second set of sensors and a second plurality of terminals subscribed to the secondary network and configured to receive commands from the secondary computer and to transmit electric orders to actuators belonging to the second set of control surface actuators, the first and second sets of sensors being disjointed, and the first and second sets of control surface actuators being disjointed. 14. The flight control system according to claim 13, wherein the back-up computer includes an independent specific control module, as a back-up specific control module, that cannot be deactivated upon outside intervention and cannot deactivate itself, each said pair of specific computation modules and the back-up specific control module sharing the second network. 15. The flight control system according to claim 1, wherein the aircraft is a fixed-wing aircraft, and the flight control system is configured to be implemented in the fixed-wing aircraft. 16. The flight control system according to claim 1, wherein the first protocol is an Avionics Full Duplex Switched Ethernet (AFDX) network protocol, and the second protocol is a protocol for at least one fieldbus according to standard MIL-STD-1553. 17. The flight control system according to claim 1, wherein one of the first primary energy source and the second primary energy source includes a generator coupled to a reactor to deliver a variable frequency voltage, and the secondary energy source includes a permanent magnet generator mechanically driven by a motor. 18. The flight control system according to claim 1, wherein the secondary energy source has a maximum output capacity less than that of both the first primary energy source and the second primary energy source. 19. The flight control system according to claim 1, wherein the primary control system includes the first set of control surface actuators and a first set of sensors associated with the first set of control surface actuators,wherein the secondary control system includes the second set of control surface actuators and a second set of sensors associated with the second set of control surface actuators,wherein the first set of actuators is disjoint with respect to the second set of actuators, andwherein the first set of sensors is disjoint with respect to the second set of sensors. 20. A flight control system for an aircraft to control a plurality of actuators adapted for actuating control surfaces of the aircraft based on information supplied by one or more of piloting members and sensors of the aircraft, comprising: a primary control system to control a first set of control surface actuators of the aircraft, the primary control system including a first primary computer and a second primary computer, each said primary computer having the same structure, with generic computation modules and being respectively powered by a first primary energy source and a second primary energy source; anda secondary control system to control a second set of control surface actuators of the aircraft, different from the first set of control surface actuators, the secondary control system including at least one secondary computer and a back-up computer, each said secondary computer having specific computation modules with an architecture specific to flight control computations and being powered by a secondary energy source,wherein the primary control system is independent from the secondary control system such that failure of the primary control system does not cause failure of the secondary control system and such that failure of the secondary control system does not cause failure of the primary control system,wherein the primary and secondary energy sources are independent from each other and are of different type of energy generating principle,wherein a first network is associated with the primary control system and a second network is associated with the secondary control system, the first network having a first protocol and the second network having a second protocol different from the first protocol, and the first network being independent from the second network,wherein the first and second primary energy sources are independent from each other,wherein each said secondary computer and the back-up computer are powered by the secondary energy source and share the second set of actuators,wherein the back-up computer shares a set of actuators and a corresponding set of sensors with said at least one secondary computer,wherein the primary control system is configured to control the first set of control surface actuators and not the second set of control surface actuators, andwherein the secondary control system is configured to control the second set of control surface actuators and not the first set of control surface actuators.