摘要 |
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. |
申请人 |
BAE SYSTEMS PLC;WHITE, NICHOLAS, JAMES;MORGAN, STEPHEN, RICHARD;CLARKSTONE, JOHN, KENNETH |
发明人 |
WHITE, NICHOLAS, JAMES;MORGAN, STEPHEN, RICHARD;CLARKSTONE, JOHN, KENNETH |