Patent ID: 7017861

Claim:
A control system for actuators in an aircraft, whereby control commands for the actuators are calculated by computers distributed in the aircraft and where each computer is arranged to receive sensor parameters via a data bus and to calculate control commands for a first actuator and for at least one additional actuator in dependence on received sensor parameters, wherein: each computer is connected to and controls only one actuator and, together with the actuator, forms a servo node with a digital interface to the data bus, the computer in each servo node is arranged to receive, via the data bus, control commands for the actuator determined by a computer in at least one additional servo node, the computer in the at least one additional servo node connected to and controlling a different actuator than the actuator in the servo node and not connected to the actuator in the servo node, the computer in each servo node is arranged to select an executive control command for the actuator in the servo node in dependence on a comparison between the control commands calculated locally in the servo node and the control commands received via the data bus, the computer is arranged to control the actuator in the servo node by means of the executive control command.