Electrical flight control system for aircraft

An electrical flight control system for controlling an aircraft, the flight control system comprising a plurality of functional subassemblies, the plurality of functional subassemblies comprising a processing subassembly determining at least one positional setpoint to be achieved by at least one aerodynamic control surface as a function of at least one command, the plurality of functional subassemblies comprising at least one actuating subassembly configured to generate, as a function of the positional setpoint, at least one actuation setpoint that is transmitted to at least one actuator,

• wherein each functional subassembly comprises at least one primary computer and at least one secondary computer that are dissimilar, at least one functional subassembly being a simplex/duplex subassembly comprising at least three identical simplex primary computers and at least one duplex secondary computer, each duplex secondary computer of a simplex/duplex subassembly comprising independent and synchronized control calculation channel and monitoring calculation channel, each simplex primary computer of a simplex/duplex subassembly having a single calculation channel, and wherein, except in the event of failure, the three primary computers of a simplex/duplex subassembly form two virtual pseudo-duplex computers.