Aircraft landing gear actuator

Details Aircraft landing gear actuator Aircraft landing gear actuator

B - Operations, Transporting

64

C

B64C 25/10 (2006.01) B64C 25/30 (2006.01) F16H 25/20 (2006.01) H02K 7/00 (2006.01)

Patent

CA 2730926

This disclosure relates to a landing gear system (10) that includes a landing gear strut (14) rotatable between stowed and deployed positions. An actuator (18) is connected to the landing gear strut, and includes main and emergency drives housed within a common body and operable independently from one another. A controller (32) in communication with the actuator (18) is configured to command the actuator between the stowed and deployed positions in response to an input. The controller (32) commands the main drive during a normal operating condition and commands the emergency drive in a failure condition of the main drive. The actuator (18) includes a body supporting emergency and main leadscrews arranged coaxially with one another. Main and emergency motors respectively are coupled to the main and emergency leadscrews. An output rod is supported by and extends from the body. The output rod is threadingly coupled to and is coaxial with the main leadscrew and configured to move axially in response to rotation of the main leadscrew. A brake selectively enables and disables the emergency drive.

Linvention concerne un système de train datterrissage, comportant une jambe de train datterrissage rotative entre des positions rentrée et sortie. Un actionneur est accouplé à la jambe de train datterrissage, et comporte des entraînements principal et durgence logés dans un corps commun et susceptibles de fonctionner indépendamment lun de lautre. Un module de commande en communication avec lactionneur est conçu pour commander celui-ci entre les positions rentrée et sortie en fonction dune entrée. Le module de commande commande lentraînement principal au cours dun état de fonctionnement normal et commande lentraînement durgence en cas détat défaillant de lentraînement principal. Lactionneur comprend un corps portant des vis-mères principale et durgence agencées coaxialement. Des moteurs principal et durgence sont respectivement accouplés aux vis-mères principale et durgence. Une bielle de sortie est portée par le corps et sétend de celui-ci. La bielle de sortie est vissée à la vis-mère principale et coaxiale à celle-ci, et est conçue pour effectuer un mouvement axial provoqué par la rotation de la vis-mère principale. Un frein active et bloque sélectivement lentraînement durgence.

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