| 摘要 |
An electric control system (1) comprises a control unit (4) which comprises a member (5) able to be actuated by a pilot and a means of load-wise protection (7), and which delivers a first deflection order representative of the action exerted by the pilot on the member (5), and of the contribution made by the means of load-wise protection (7), an actuator (11) which moves said control surface (2) about an axis (Z-Z), as a function of a deflection order, and a correction device (12) which comprises a means (13) for determining a second deflection order making it possible to limit the load, to which a stabilizer element of the aircraft is subjected, to a maximum load, and a means (14) for choosing one of the first and second deflection orders, which is transmitted to said actuator (11) so as to move said control surface (2).
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