Patent ID: 8761969

Claim:
A flight control system for an aircraft, comprising: at least one actuator to actuate a mobile flight surface of the said aircraft; a flight control module in communication with the said actuator, and comprising at least a first and a second single-path computer, each configured to calculate a control command established according to at least one predetermined law for control of the flight surface, the first and second single-path computers being connected to the actuator via a control path and a monitoring path, commands to cause an action to be executed on the mobile surface being provided to the actuator via the control path, the monitoring path being used to provide comparison values to the actuator to determine whether the commands received via the control path are valid, wherein said actuator comprises logic in the control path to compare commands received from the computers via the respective control and monitoring paths and to determine on the basis of these commands an action to be executed on the mobile surface, and the logic includes a voting architecture, the first computer belonging to a first group of computers, the second computer belonging to a second group of computers and the voting architecture having a first voting level for each of said first and second groups and a second voting level at outputs the first and second groups.