| 摘要 |
<p>The aircraft direction controller (116) is equipped with at least two drivers, each having at least two servo-controls (110, 112, 114), each having at least an electrical control input (111a, 113a, 115a), and an electrical drive system for the servo-controls designed to occupy a first state corresponding to a normal operation of the engines in which at least one of the servo-controls actuates the controller. At least one of the servo-controls (115), called the mixed servo-control, has in addition a mechanical control input (115b). In addition the electrical drive for the servo-controls is designed to occupy a second state, corresponding to an engine failure, in which at least two of the servo-control actuate simultaneously the controller (116), and to occupy a third state corresponding to an electrical failure, in which the mixed servo-control (115), driven from the mechanical control input, actuates the controller (116).</p> |
