An actuator control system(9) for coupling to one or more flight control computers (FCCs) (11, 12,13, 14); comprising:apparatus for controlling an aerodynamic control surface in response to commands received from one or more FCCs, and, integrated with the controlling apparatus, a failure protection system (6) comprising apparatus arranged to provide at least one of the following functionalities: a servo monitor functionality (30), a command monitor functionality (32), and a loop closure functionality (36). Thus, in the overall flight control system (1), some or all of the elements of the failure protection system are located in the actuator control stage.
Actuator control system
2015-09-17
Patent
Electronic Resource
English