Procedure and system to move the elevator of an aircraft

Details Procedure and system to move the elevator of an aircraft Procedure and system to move the elevator of an aircraft

B - Operations, Transporting

64

C

B64C 13/50 (2006.01) B64C 9/00 (2006.01) G05D 1/00 (2006.01)

Patent

CA 2437216

- 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).

- Le système de commande électrique (1) comporte une unité de commande (4) qui comprend un organe (5) susceptible d'être actionné par un pilote et un moyen de protection en effort (7), et qui délivre un premier ordre de braquage représentatif de l'action du pilote sur l'or- gane (5) et de la contribution apportée par le moyen de protection en effort (7), un actionneur (11) qui déplace la gouverne (2) autour d'un axe (Z-Z), en fonction d'un ordre de braquage, et un dispositif de cor- rection (12) qui comprend un moyen (13) pour déterminer un second ordre de braquage permettant de limiter l'effort, auquel est soumis un élément stabilisateur de l'aéronef, à un effort maximal, et un moyen (14) pour choisir l'un des premier et second ordres de braquage, qui est transmis audit actionneur (11) pour déplacer ladite gouverne (2).

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