Slat deployment mechanism

B - Operations – Transporting – 64 – C

Patent

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Details

B64C 9/22 (2006.01)

Patent

CA 2719173

An aircraft slat deployment mechanism comprising: a first drive member (4) coupled to the slat at a first pivot point (5); and a second drive member (6) coupled to the slat at a second pivot point (7) which is offset from the first pivot point. A first rack is provided on the first drive member, and a first pinion (11) is carried by the drive shaft (10). The first pinion (11) is ar-ranged to transmit mechanical power from the drive shaft (10) to the first drive member (4) via the first rack. A second rack is provided on the second drive member (6), and a second pinion (12) is carried by the drive shaft (10). The second pinion has a differ-ent radius to the first pinion. The second pinion is arranged to transmit mechanical power from the drive shaft to the second drive member via the second rack, such that the second drive member moves at a different speed to the first drive member.

Mécanisme de braquage de bec daéronef, comprenant : un premier organe de commande accouplé au bec au niveau dun premier point de pivot; et un deuxième organe de commande accouplé au bec au niveau dun deuxième point de pivot décalé par rapport au premier point de pivot. Le premier organe de commande est équipé dune première crémaillère et larbre de commande porte un premier pignon. Le premier pignon est conçu pour transmettre lénergie mécanique de larbre de commande au premier organe de commande par lintermédiaire de la première crémaillère. Le deuxième organe de commande est équipé dune deuxième crémaillère, et larbre de commande porte un deuxième pignon. Le rayon du deuxième pignon est différent de celui du premier pignon. Le deuxième pignon est conçu pour transmettre lénergie mécanique de larbre de commande au deuxième organe de commande par lintermédiaire de la deuxième crémaillère, de façon à ce que le deuxième organe de commande se déplace à une vitesse différente de celle du premier organe de commande.

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