Shock absorber for aircraft landing gear

B - Operations – Transporting – 64 – C

Patent

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Details

B64C 25/60 (2006.01) F16F 9/06 (2006.01)

Patent

CA 2691212

The invention relates to a shock absorber for the landing gear of an aircraft, including two members (1, 2) mounted so as to be capable of telescopically sliding one in the other and defining an inner volume filled with a hydraulic fluid and a gas and divided into at least two chambers (7, 8) by a partition (5) including at least one throttling opening (10) through which the hydraulic fluid passes from chamber to chamber, in particular upon a compression of the shock absorber. According to the invention, the partition includes at least one degassing opening for allowing the gas to transfer from one chamber to the other when the landing gear is in the extended position, the degassing opening being vertically offset relative to the throttling opening so as to be located above the latter when the landing gear is in the extended position.

L'invention concerne un amortisseur pour atterrisseur d'aéronef ayant deux éléments (1,2) montés pour coulisser télescopiquement l'un dans l'autre et définissant un volume interne rempli de fluide hydraulique et de gaz et séparé en au moins deux chambres (7,8) par une séparation (5) comportant au moins un orifice de laminage (10) par lequel le fluide hydraulique transite d'une chambre à l'autre notamment lors d'une compression de l'amortisseur. Selon l'invention, la séparation comporte au moins un orifice de dégazage pour permettre le transfert de gaz d'une chambre à l'autre lorsque l'atterrisseur est en position déployée, l'orifice de dégazage était décalé en hauteur par rapport à l'orifice de laminage pour se trouver au dessus de ce dernier lorsque l'atterrisseur est en position déployée.

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